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NASA TECHNICAL 

MEMO RAN D U M 



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1 NASA TM X-1507 






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INVESTIGATION OF A 

AXISYMMETRIC INLET SYSTEM 
CAPABLE OF HIGH PERFORMANCE 
AT MACH NUMBERS 0.6 TO 30 



by Norman E. Sorensen and Donald B. Smeltzer 

Ames Research Center 
Moffett Field, Calif. 



NATIONAL AERONAUTICS AND SPACE ADMINISTRATION • WASHINGTON, D. C. • FEBRUARY 1968 






NASA TMX-1507 



INVESTIGATION OF A LARGE-SCALE MIXED-COMPRESSION 

AXISYMMETRIC INLET SYSTEM CAPABLE OF HIGH 

PERFORMANCE AT MACH NUMBERS 0.6 TO 3.0 

By Norman E. Sorensen and Donald B. Smeltzer 

Ames Research Center 
Moffett Field, Calif. 



NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 

For sole by the Clearinghouse for Federal Scientific and Technical Information 
Springfield, Virginia 22151 - CFSTI price $3.00 



TABLE OF COOTEmS 

Page 

SUMMARY 1 

lOTRODUCTION 2 

SYMBOLS 2 

DESIGN h 

MODEL AND INSTRUMENTATION 6 

MEASUREMENT TECHNIQUES AND ACCURACY 7 

RESULTS AND DISCUSSION 7 

CONCLUDING REMARKS I3 

APPENDIX A - PLOTTED DATA ±k 

APPENDIX B - METHOD OF DETERMINING THE GPTIMOM COMRTNATTON OF 

TRANSONIC ADDITIVE DRAG AND TOTAL -PRESSURE RECOVERY 15 

REFERENCES I6 

TABLE I.- INLET COORDINATES 17 

TABLE II,- ENGINE -FACE PRESSURE RECOVERY DATA, Pt /Pt ^^ 

FIGURES 65 



IIWESTIGATION OF A LAEGE-SCALE MIXED-COMPRESSION 

AXISYMMETRIC II^ET SYSTEM CAPABLE OF HIGH 

PERFORMANCE AT MACH NUMBERS 0,6 TO S-O"^ 

By Norman E. Sorensen and Donald B. Smeltzer 

Ames Research Center 

SUMMARY 



A model of a mixed-compression inlet with a 20 -inch-diameter capture area 
was designed and tested in combination with three subsonic diffuser designs. 
The shortest inlet system was about I.50 capture diameters long measured from 
the cowl lip to the engine face and employed vortex generators just downstream 
of the throat to reduce the total pressure distortion at the engine face. The 
other two systems were 1.75 capture diameters long and did not employ vortex 
generators. The supersonic portion of the inlet was designed for Mach num- 
ber 3.0 and was capable of performing at off -design Mach numbers by transla- 
tion of the cowl. The major objective was to investigate relatively short 
axisymmetric inlet systems capable of high performance over the complete Mach 
number range. The model was tested in a wind tunnel at Mach numbers from 0.6 
to 3.2 and angles of attack from 0*^ to 8^. The Reynolds number was about 
2X10® per foot at Mach number 3.0. 

The supersonic diffuser of the inlet was designed with the aid of a com- 
puter program employing the method of characteristics. Preliminary tests 
showed that the supersonic portion of the inlet performed as predicted^ but 
the flow separated in the subsonic diffuser limiting the performance at the 
engine face. The subsonic diffuser was then modified and the total-pressure 
recovery was raised to 90 percent with about 11 percent boundary-layer bleed 
mass flow from 86-percent recovery with 13-percent bleed. Off -design total- 
pressure recoveries were also improved about h percent over the Mach number 
range 1.55 to 3.0. The I.50 capture diameter inlet^ with vortex generators^ 
showed an additional 1-percent improvement in recovery^ but of more signifi- 
cance was the reduction in total pressure distortion at the engine face. The 
distortion was reduced to 6 to 7 percent from about 10 percent and the maximum 
recovery was improved to about 91 percent with about 11-percent boundary-layer 
bleed mass flow. Without the generators the distortion of the 1.50-diameter 
inlet was about doubled (l^ percent). 

The test results in the Mach n-umber range 0.6 to 1.2 included details of 
experimentally measured additive drag. It was found that there was an optimum 
trade of additive drag for pressure recovery. 



■^itle^ Unclassified. 



INTRODUCTION 



One of the important elements of a supersonic propulsion system is the 
inlet. Satisfactory performance of the system usually depends upon a high 
level of inlet performance not only at the conditions for which the system has 
been optimized^ but as in the case of a supersonic transport vehicle^ over the 
entire mission. When the performance of a vehicle is considered^ the weight 
of the inlet is important. A short inlet ^ of course^ tends to weigh less than 
a long inlet; but also tends to make high performance difficult to attain. 
This has presented a challenging problem^ the solution of which was approached 
through a theoretical and experimental research program with a large-scale 
axisymietric inlet model. The major objective of the program was to investi- 
gate relatively short axisymmetric inlet systems theoretically capable of high 
performance over a wide range of Mach numbers. 

The axisymmetric inlet model chosen for study was a mixed compression 
type. The supersonic portion of the inlet was designed for Mach number 3.0. 
Performance at off -design Mach numbers was accomplished by translation of the 
cowl. Three variations in subsonic diffuser design were tested in combination 
with virtually the same supersonic diffuser. The initial subsonic diffuser 
proved to be deficient ^ as indicated by preliminary test results ^ and led to a 
modification which produced more satisfactory results. A shorter subsonic 
diffuser was then designed and tested with vortex generators. The generators 
were mounted just downstream of the throat region to reduce the total pressure 
distortion at the engine face. Boundary -layer bleed configurations were 
developed for Mach number 3*0 and were tested at off -design Mach numbers with- 
out change. By controlling the bleed plenum chamber pressures ^ a range of 
bleed mass -flow ratios was investigated for a given bleed configuration. 
Tests were conducted over the Mach number range 0.6 to 3.2 at a tunnel total 
pressure of 30 inches of Hg. This corresponded to a Reynolds number of about 
2X10® per foot at Mach number 3.0. The tests were conducted primarily to 
determine the performance parameters of engine-face total-pressure recovery 
and distortion as a function of boundary-layer bleed mass -flow ratio at angles 
of attack from 0° to 8^. The transonic tests included experimental determina- 
tion of the additive drag. Theoretical predictions based upon the method of 
characteristics were compared with the experimental results. A small portion 
of the results presented herein is also presented in references 1 and 2. 



SYMBOLS 

A (3 capture area^ 31^ -16 sq_ in. 

A^ local duct area normal to the inlet centerline^ sq. in. 



"b span of the vortex generators ^ in» 

Ct) additive drag coefficient "based on A^ 
a 

CprjT net -thrust coefficient iDased on A^^ 

D capture diameter^ 20 in, 

h local rake height^ in. 

^ free -stream Mach number 

Z^v^ free -stream Mach number decrement from the design Mach number 

M^ local Mach number 

m mass flow 

P^ total pressure 

p static pressure 

Pt2 " ^t2 

Ap-h total pressure distortion parameter^ -^ 



'lip 



Pt, 



r local radius 



R capture area radius 



X axial distance from the tip of the centerbody 
R capture area radius 

x\ axial distance from the cowl lip 
Ryp capture area radius 



axial distance from the cone tip to the cowl lip 
capture area radius 



-r- incremental — 



a angle of attack^ deg 

(X incipient unstart angle of attack; deg 

(") average values 



Subscripts 

inlet lip station 

1 throat station 

2 engine -face station 
bl bleed 

2 local flow 

00 free -stream conditions 

Note: The letters A; B^ C^ and D^ referring to the boundary -layer bleed exit 
settings ; denote a progressively more restricted bleed flow from A^ the 
fully open exit setting^ to D^ the most restricted setting. The letter 
A' refers to a bleed exit setting associated only with the 1.75 D 
modified inlet . 



DESIGN 



Satisfactory performance of a propulsion system usually demands a rela- 
tively short inlet capable of high performance at off -design IVIach numbers as 
well as at the design Mach number. The rec^uirement for adequate transonic 
acceleration led to a design which employed a low-angle conical centerbody to 
keep the transonic additive drag reasonably small. The requirement for high 
performance at off-design Mach numbers was compatible with the transonic 
requirements and led to a supersonic diffuser design with high performance. 
For the shortest subsonic diffuser the use of vortex generators was vital in 
achieving low flow distortion at the engine face. The design of the inlet 
system divided naturally into two parts ^ the supersonic diffuser and the 
subsonic diffuser. 



Supersonic Diffuser 

This portion of the inlet was designed with the aid of a computer program 
that employed the method of characteristics. The program proved to be ade- 
quate and is fully described in reference 3* Figure 1 shows the diffuser con- 
tours with the theoretical network of characteristics and flow properties from 
the computer program. An initial internal cowl angle of 0^ and a 12.5^ half- 
angle conical centerbody were selected to satisfy the important external 
requirements for low transonic additive drag and low cowl drag. The rest of 
the contours to the throat were adjusted by trial until the computer program 
gave the desired theoretical conditions at the throat and sufficiently low 
pressure rises across the internal shock -wave impingements to prevent 
boundary-layer separation. The goal was to attain uniform flow in the throat 
at a Mach number of I.3 and a pressure recovery above 95 percent. Figure 1 
shows that this goal was closely achieved. In addition^ the pressure ratios 



across the first and second shock -wave impingements on the centerbody were 
2.c30 and 1.68^ respectively^ and 2.13 on the cowl. These pressure ratios were 
judged (on the basis of ref. h) to be below those for incipient separation of 
the expected boundary layers. The off -design air flow requirements of a 
selected turbofan engine were satisfied throughout the Mach number range. The 
inlet provided ^0.5 percent of the capture mass flow at JVlach number 1.0. This 
may not be sufficient for some engines^ but a contracting centerbody version 
of the inlet could provide higher mass flow at all speeds. An additional 
restraint imposed upon the theoretical design was the requirement that the 
axial distance through which the cowl had to be translated for off -design 
operation be kept to a minimum. For this inlet^ the translation distance 
required was about 10 inches or half an inlet diameter. This was believed to 
be short enough to avoid excessive weight penalties. 



Subsonic Diffuser 

Since most of the performance deficiencies found in the initial tests 
were associated with losses in the throat and subsonic diffuser^ three differ- 
ent subsonic diffusers were tested in combination with virtually the same 
supersonic diffuser. These three designs are shown in figure 2. The initial 
diffuser and its modification are shown in figure 2(a). The initial diffuser 
was designed with a linear variation of area from the beginning of the throat 
at x/R = 3*75 to the engine -face station at x/r ^ 6.0^. The modified dif- 
fuser was designed to have a linear static-pressure variation between these 
stations. The modified design provided a lower rate of expansion downstream 
of the throat to x/r = 5-20 than did the initial design. After this point 
the flow expanded rapidly. Because the changes in area distribution between 
the initial and modified diffusers were accomplished for reasons of expediency 
by changes in the centerbody dimensions only^ the minimum area did not remain 
fixed relative to the cowl when the cowl was translated for off -design opera- 
tion. It was recognized that shifting of the minimum area with translation 
was undesirable^ especially from an inlet control standpoint. However^ the 
design was tested mainly to determine the difference in performance with the 
two diffusers at the design lyiach number. The inlet for these two diffusers 
was about 1.75 diameters long measured from the cowl lip to the engine-face 
station. The success attained with this modified diffuser led to the design 
of a shorter subsonic diffuser providing an inlet about I.50 diameters long^ 
as shown in figure 2(b). The diffuser had a linear variation of Mach number 
from the beginning of the throat at x/r = 3.75 to the final diffusion Mach 
number of about O.3 at the engine-face station^ x/r ^ 5*50. This design pro- 
vided a slightly lower rate of expansion in the throat region than did the 
diffuser modified to yield a linear static pressure variation. In addition^ 
the throat (x/r = 3.75) did not shift with translation. 

The coordinates of the inlets are presented in table I. The contours for 
the 1.75 D inlets include compensation for boundary-layer growth from the 
points of the first shock wave impingements on the cowl and centerbody to the 
throat. The contours for the I.50 diameter inlet were based on inviscid 
calculations only. 



MODEL AKD INSTRUMENTATION 

The model with a 20-inch capture diameter was as large as practical for 
installation in the Unitary Plan wind tunnels at Ames Research Center. 
Sketches of the model and instrumentation are shown in figure 3^ and a photo- 
graph of the model mounted in the 11-foot transonic wind tunnel is shown in 
figure h. For structural reasons^ the inlet area was varied by translating 
the cowl rather than the centerbody. The cowl had a sharp 15° liP and could 
be translated about l8 inches as shown in figure 3(a). The outer shell was 
attached to four hollow struts mounted on the centerbody sting support. The 
main duct exit area was controlled by a translating sleeve and a fixed plug. 
Figure 3(b) shows details of the bleed system. Four separate bleed zones are 
indicated, each of which had separate and controllable exits allowing the 
bleed flow to be controlled from maximum flow to no flow. Also^ separation of 
the zones prevented recirculation of the flow from the higher pressure zones 
in the throat (zones III and IV) through the lower pressure zones upstream 
(zones I and II) . To insure low back pressure at the bleed exits, exit fair- 
ings shown in figure 3(a) were provided. The forward bleed areas were 
designed to be just ahead of the shock -wave impingements shown in figure 1. 
On the basis of the results in reference 5^ this appeared to be an effective 
means of controlling the boundary-layer growth. Distributed bleed in the 
throat region provided a variation of bleed flow as the terminal shock wave 
progressed into the throat region. The porosity of all of the bleed areas was 
^1.5 percent. The diameter of the holes in bleed zone I was 0.025 inch. The 
diameter of the holes in the remaining zones was 0.125 inch. 

The instrumentation was conventional but rather detailed. The main duct 
instrumentation consisted of six total -pressure rakes for measuring the total- 
pressure recovery at the simulated engine face. Each rake had six tubes 
spaced so as to provide an area weighted average total pressure as shown by 
the sketch in table II. Static pressure rakes (see fig. 3(a)) were stationed 
near the main duct plug which, in conjunction with the known area at this sta- 
tion and the choked main duct exit area, allowed computation of the main duct 
mass flow. Static pressure orifices were located in a row along the top inner 
surfaces of the cowl and centerbody to the end of the subsonic diffuser. Two 
boundary-layer rakes were located on the centerbody and one on the cowl as 
shown in figure 3(b). Two pitot pressure rakes at the beginning of the throat 
measured the performance of the supersonic diffuser. Bleed flow rate in the 
centerbody boundary -layer removal ducts was measured by three total- and 
static-pressure rakes in the outer duct and four in the inner duct. Bleed 
flow rate measurements through the two zones on the cowl surface were made by 
the use of measured plenum chamber pressures and the known choked exit areas. 
Pressures were also measured in the centerbody plenum chambers. For the tran- 
sonic tests ^ four rakes were installed at the point of maximum centerbody 
diameter. Pressure measurements from these rakes were used to calculate both 
the inlet mass flow and the total momentum change from the free stream to the 
inlet lip. 

Vortex generators were installed about two throat heights downstream from 
the beginning of the throat of the I.50 diameter inlet. Forty generators were 
mounted on the centerbody and 5^ on the cowl. Other details of the generators 



are showi in figure 3{^) * The vortex generators were selected in accordance 
with reference 6. Vortex generators were not used with the 1.75 diameter 
inlet systems . 



MEASUBEiy[E]OT TECHNIQUES AM) ACCURACY 

As with most inlet tests of this type^ a problem was encountered in accu- 
rately determining the mass -flow rates through both the main duct and the var- 
ious bleed systems. The calibration factor for the main duct flow metering 
system was found to vary with main duct plug position^ Mach number^ and bound- 
ary layer bleed mass flow. No calibration factor was found that would yield 
better than approximately ±2 percent accuracy in the main duct mass flow. 
Special care was taken in calibrating the bleed mass -flow measuring systems. 
Each system was calibrated in the wind tunnel at Mach 3.0 and a =^ 0. The 
techniq^ue consisted of varying each bleed exit from open to fully closed and 
then plotting the computed bleed mass -flow ratio against the incremental 
change in main duct mass flow. This method yielded bleed calibration factors 
which gave consistent results when all the bleed mass -flow rates were summed 
and compared to the difference between the known capture flow (mQ/n^ = 1.000 
at M^ = 3.0) and the measured engine-face mass flow. The bleed flow calibra- 
tion factors thus determined were used for data reduction at all Mach numbers. 
No attempt was made to calibrate the bleed flow measuring systems at angle of 
attack^ but the calibration factors were believed to be as accurate at 2^ as 
at 0^. In the transonic Mach number range from 0.6 to I.3 bleed flow was not 
measured. For the transonic tests the inlet mass flow was measured by the 
four rakes mounted just ahead of the throat (see fig. 3(b)). Additive drag 
was computed by the methods described in reference T^ from the total momentum 
change of the inlet mass flow (determined from the rake measurements)^ pres- 
sure forces on the compression surfaces, and estimated friction forces acting 
on the surfaces. All other measurement techniques were conventional and the 
estimated acci]r*a.pv of thp mppic^n-rf^ri nnnn-t-.i+.if=ic: 1 c: QQ follows! 

Accuracy at a = 0^ ±0.005 ±0.005 ±0.1^ ±0.2 ±0.05 

Tunnel total pressure was 15 psia for all tests. 



RESULTS AND DISCUSSION 



Much of the data obtained was of limited interest and has been plotted in 
appendix A or tabulated in table II. The method for determining optimiom per- 
formance based upon a combination of transonic additive drag and total- 
pressixre recovery is discussed in appendix B. The discussion to follow has 
drawn certain results from these appendixes for comparison and illustration of 
the more significant factors. 



Most of the inlet development effort vas directed toward attaining higli^ 
performance at the design Mach numloer of 3.0. The bleed configurations and 
the bleed exit settings that controlled the bleed -flow rates vere established 
at Mach number 3.0^ and the inlets were tested without change of the bleed 
exit settings at off -design Mach numbers. No attempt was made to improve the 
off -design performance with other boundary-layer bleed configurations. The 
modified version of the initial diffuser (1.75 B) was not considered suitable 
for off -design operation since its throat did not remain fixed relative to the 
centerbody at off -design conditions. Most of the results presented for this 
design are therefore limited to Mach number 3-0- The results for the 1.50 
diameter inlet are presented in more detail since the throat remained fixed 
relative to the centerbody throughout its operating range. The presentation 
of the transonic results is treated differently from the results at higher 
Mach numbers because a determination of the trade-off of experimental additive 
drag versus pressure recovery at the engine face was required in order to 
optimize net propulsive thrust. This involved the use of typical engine data 
and an assumed flight profile to obtain realistic values of thrust. The 
optimization procedure is presented in appendix B. 

Performance at M^ ^ 3*0 

Because of control margin requirements an actual propulsion system may 
not operate at the maximum inlet pressure recovery. However^ the maximum 
recovery serves as an indicator of the capability of the inlet. All inlets 
were designed with a throat Mach number of 1.3^ but a lower Mach number (1.2 
or less) was required to achieve maximum pressure recovery. For tests of the 
initial and modified inlets (1.75 D) this occurred with the bow shock wave 
impinging 0.075 x/r inside the cowl lip. This represented more geometric 
contraction than was expected even allowing for the lower throat Mach number 
of 1.2 or less. The additional contraction was thought to be caused by over- 
compensation of the boundary layer due to the geometric compensation intro- 
duced into the contours. For this reason compensation was not included for 
the shorter inlet (1.50 D) . For this inlet maximum pressure recovery was 
attained with the bow shock wave impinging only O.OU5 x/r inside the cowl 
lip. This again represented an additional contraction required to obtain max- 
imum pressure recovery. With the inlet system operating under these condi- 
tions and with the terminal shock wave systems in the more forward position in 
the throaty an envelope of the maximum pressure recovery and corresponding 
total pressure distortion measured for several combinations of bleed exit set- 
tings and bleed configurations is presented in figure 5* For the initial 
tests a maximum recovery of 86 percent with I3 -percent bleed mass flow and 
about lO-percent distortion at the engine face was attained. Since recoveries 
as high as 97 percent were measured for the supersonic diffuser^ the main loss 
in performance was attributable to flow separation in the throat and subsonic 
diffuser. This led to the modification of the subsonic diffuser from one 
based on a linear area variation to one which gave a linear static pressure 
variation. This greatly reduced the initial rate of diffusion in the throat 
region as shown in figure 2(a). With the modified diffuser a range of maximum 
recoveries was attained up to a little over 90 percent with about 11 -percent 
bleed (fig. 5). For this condition the distortion was about 10 percent^ the 
lowest attained with this diffuser- With the shorter diffuser employing 



vortex generators^ the distortion T^as lowered to between 6 and 7 percent for 
the same bleed flow while the recovery was increased about 1 percent to 
91 percent. This latter result was attributable to the better distribution of 
the flow energy induced by the vortex generators through turbulent mixing of 
the high energy core flow with the boundary layer in the throat. Results of 
supercritical operation for the modified and I.50 diameter inlet systems are 
compared in figure 6. They show a continuation of the better performance with 
the 1.50 D inlet. Not only did the recovery remain about 1 percent better as 
the terminal shock wave system moved downstream^ but the distortion also 
remained at or below 10 percent over the useful supercritical range. This was 
a typical result with vortex generators as can be seen in figure 7 where the 
results for four bleed exit settings are plotted. These curves show that the 
performance is still largely a function of boundary-layer bleed. The effect 
of the vortex generators is shown by comparison of the performance with and 
without generators shown in figure 8. The use of vortex generators in this 
short diffuser improved the pressure recovery by about 1 percent, but more 
significantly, the distortion was markedly reduced from about 16 to about 
7 percent for conditions near maximum recovery. An examination of the 
detailed pressure recovery plots from the engine -face rakes shown in figure 9 
reveals the nature of the distortion for the maximum pressure recovery points 
of the previous figure. Radial distribution of pressure recovery for each of 
the six engine -face rakes is plotted and shows radial distortion values as low 
as 2 percent. The greatest radial distortion with the vortex generators 
installed was u.3 pex*cenL \, rake no. o; which was about eq^ual to the totaj_ dis - 
tortion (fig. 8). This suggests that local tailoring of the generators or 
inlet contours or both might reduce the total distortion to 5 percent or less. 
Because distortions this low appear possible and since most engines are 
designed to operate without any performance penalty with up to 10 percent 
distortion, even shorter subsonic diffusers may be practical. 

Figure 10 shows typical variations with engine face total-pressure 
recovery of the bleed flow through the individual bleed zones. Bleed in the 
region of the throat (zones III and IV) changed with engine-face pressure 
recovery as a result of the change in position of the terminal shock wave in 
the throat. As the terminal shock wave moved upstream into the throat area 
and passed over the bleed holes, the higher pressures behind the terminal 
shock wave forced more air out of the bleed holes. The change in engine-face 
mass flow with pressure recovery was thus due almost entirely to the change in 
bleed flow through zones III and IV. (The bleed flow through zone II can 
increase slightly with the terminal shock wave in its most forward position.) 
As illustrated by the data of figure 10, the boundary-layer removal required 
from the centerbody surface was greater than that required on the cowl. This 
was because of the relatively longer boundary-layer rim on the centerbody and 
the two shock impingements on the centerbody boundary layer whereas only one 
occurred on the cowl. Boundary-layer measurements at several stations on the 
cowl and centerbody are shown in figure 11. Comparison of the pitot pressure 
profiles at the two stations on the cowl surface indicated that the boundary 
layer was thin and well controlled by the bleed through zone I. On the cen- 
terbody a similar comparison showed considerably thicker boundary layers at 
the throat survey station. The relatively thick boundary layer in the throat 
was believed to be caused in part by the lack of boundary-layer removal near 
the first shock -wave impingement on the centerbody. Comparison of the 

9 



boundary-layer pitot pressure profiles shown in figure 11 on the centerbody 
ahead of and "behind this impingement (approximately x/r = 3. 200) indicates a 
sudden thickening of the boundary layer but does not indicate separation. 
Consequently^ about two-thirds of the total bleed was required on the 

centerbody. 

When the performance penalties associated with boundary-layer removal are 
estimated, it is necessary to consider the amount of bleed and also the total- 
pressure recovery of the bleed flow because the ducting required for the bleed 
flow is smaller with higher recoveries^ and the bleed exit momentum recovery 
potential is greater. Both factors help to minimize the propulsion system 
weight and drag. Figure 12 shows typical boundary-layer bleed plenum chamber 
pressure ratios for each zone for the "B" exit setting. Fortunately, the 
zone IV centerbody bleed^ which had the highest flow rate^ also had the high- 
est recovery. In addition^ the increase in recovery for zone IV with increas- 
ing bleed was favorable because^ as shown in figure 10^ the increase in total 
bleed was mostly through zone IV. 

Some of the effects of the terminal shock wave system on bleed flow vari- 
ation have been discussed, but little knowledge of the shock -wave position can 
be gained without examination of static pressure distributions. For this pur- 
pose three typical distributions for the I.50 diameter inlet are presented in 
figure 13 to show the positions of the shock waves at three levels of perfor- 
mance. These distributions correspond to performance data shown in figure 6. 
The measured supersonic static pressure distributions agree reasonably well 
with the theoretical distributions shown in figure 1, although direct compari- 
son cannot be made because of differences in cowl position. For the experi- 
mental results the cowl was translated 0.0^5 ^/^ forward of the theoretical 
design position of figure 1. The theoretically sharp pressure rises at the 
shock wave reflection points were masked somewhat by the boundary layer, 
especially in the throat region where the terminal shock wave was in the posi- 
tion for maximum pressure recovery (fig. 13(a)). When the shock wave was far- 
ther downstream (figs. 13(h) and (c)) the terminal shock wave pressure rise 
started close to the predicted pressure level (p/p^ ~ 13 •O) ^^^ extended over 
some length as is characteristic of a shock wave train. As the terminal shock 
train moved downstream (figs. 13(b) and (c)) the pressure recovery and bleed 
mass flow progressively decreased as shown in figure 6. As the shock train 
moved out of the throat region in which the bleed removal holes are located, 
there was no longer any change in bleed flow and the pressure recovery 
decreased rapidly. By altering the bleed hole distribution in the throat it 
should be possible to change the variation of bleed flow with pressure 
recovery to some extent. 

The previous discussion considered only the steady-state performance at 
0° angle of attack. Of equal importance is the resistance of the inlet to 
unstarting which might be caused by sudden changes in approaching flow condi- 
tions similar to those associated with gusts. A gust can change the local 
angle of attack suddenly by 2^ or more. If an inlet can be pitched to this 
angle or greater without unstarting^ it should be relatively insensitive to 
sudden changes in angle of attack of this order. When operated supercriti- 
cally with some recovery penalty, the present inlets have remained started up 
to an angle of attack of 3.5^» To illustrate this, figure 1^ has been 

10 



prepared in vhich the pressure recovery for exit settings A^ B^ and C from 
figure 7 has "been replotted. To facilitate understanding of these curves a 
detailed explanation of the curve for bleed exit setting A is described. The 
data points were obtained at 0*^ angle of attack. Starting at 0° the angle of 
attack was increased until the inlet unstarted. At maximum pressure recovery 
(which represents the most forward position of the terminal shock wave system) 
a.n angle of attack of 0.5*^ unstarted the inlet as shown on the curve. If the 
pressure recovery were degraded a small amount (representing downstream with- 
drawal of the terminal shock wave system) ^ the angle of attack could be 
increased to ot^ - 1.5*^ before the inlet unstarted. Further reducing the 
pressure recovery allowed the angle of attack to be increased to a limiting 
value of ocu " 3*8*^* ^"t this point further reducing the pressure recovery had 
no effect on o^j^; it remained constant at 3-8*^* 

Another characteristic of a gust besides suddenly changing the local 
angle of attack is the possibility of a reduction of the local Mach number. 
With the inlet operating at peak performance^ the throat Mach number was 1.2 
or lower; Jience^ a slight reduction in local external Mach number could cause 
the throat to choke (M-^h "^ 1»0) which would result in unstarting the inlet. 
Figure 15 shows the maximam recovery of the I.50 D inlet for several lip posi- 
tions^ the highest recovery corresponding to the (x/R)]_j_p - 2.33O position. 
Plotted in the lower part of the figure is the Mach number decrement from Mach 
number 3-0 that the inlet can experience before unstarting. (This curve was 
u.enveu j-roiu one j-ower curve xn j.xgure a.^*j For instance^ witn tne j_ip at 
position (x/r)]_-j_p = 2.^00 the inlet remains started as the Mach number is 
decreased from 3-0 to 2.8. It can be seen that if a gust causing a 0.1 decre- 
ment in local Mach number is to be tolerated^ the inlet contraction ratio must 
be reduced so that the maximuin inlet recovery is degraded about 1.5 percent. 

The cowl lip translation required to restart the inlet is plotted in fig- 
vcre 16 for Mach numbers 1.55 to 3*2. Also shown for comparison is the theo- 
retical lip position for restart which shows that the inlet started with less 
cowl translation than predicted. This favorable result was ascribed to the 
bleed flow removed from zones I and II upstream of the throat which decreased 
the amount of flow that the throat had to pass allowing the inlet to restart 
with less translation. Because of thiS; the inlet was self starting (no 
translation required) at JV^ = 1^55» 

The maximum pressure recovery and flow distortion of the I.50 D and the 
modified 1.75 B inlets are compared up to 8^ angle of attack in figure YJ. 
When the inlet was operated at angle of attack^ the maximum pressure recovery 
attainable was less than at a = 0*^ as indicated. The performance of both 
systems deteriorated rapidly above 2*^^ but the recovery of the shorter inlet 
was about 1 percent better up to 5^« Above 5*^ the distortion in the shorter 
inlet became more serious and the pressure recovery reduced accordingly. 

To match an inlet to an engine it is important to know the engine -face 
mass-flow capability at angle of attack. This capability is presented in fig- 
ure 18 for the B bleed exit setting. It can be seen that up to 5*^ the mass- 
flow capability remained fairly high^ but at 8° the flow was seriously reduced 
and accompanied by high flow distortion. As mentioned in the section for 
Accuracy^ no attempt was made to calibrate the main duct and bleed flow at 

11 



angle of attack^ and the error involved in the main duct mass flov at angles 
of attack above 2° may be as much as 5 percent. The mass -flow values shown ^ at 
angle of attack should therefore be treated as qualitative. 



Off -Design Performance 

Maximum performance of the three inlets is shown in figure 19 for Mach 
numbers from 0.6 to 3.2. The recovery for the initial inlet remained about 
h percent lover than that for the other two inlets from Mach numbers 1.55 to 
3.0. This was attributed to flow separation caused by the rapid initial 
expansion in the subsonic diffuser as previously mentioned. Use of a linear 
static pressure variation in the design of the subsonic diffuser provided a 
low initial rate of expansion in the throat region and produced good perfor- 
mance at design and off -design Mach numbers even though the throat shifted 
with translation as shown in figure 2(a). The I.50 D inlet with vortex gener- 
ators was designed so that the throat did not shift with translation (see 
fig. 2(b)) and incorporated the low initial rate of expansion in the subsonic 
diffuser. Its recovery was generally equal to or about 1 percent higher than 
the modified inlet and the distortion was considerably lower throughout most 
of the Mach number range. It should be pointed out that the data for 
M^ - 3.2 were obtained with the contraction ratio corresponding to that for 
maximum recovery at M^^ - 3.0. Model design features prevented translating 
the centerbody to increase contraction ratio which would have increased the 
pressure recovery. The transonic results from Mach niunbers 0.6 to 1.2 were 
obtained from an optimization procedure with a selected engine as described in 
appendix B. The transonic data show that the distortion for the shorter inlet 
with the generators was reduced by about 2.5 percent from that of the modified 
inlet . 

One of the prime concerns in the transonic range was the need for low 
additive drag as pointed out in the discussion of the design. The considera- 
tion of drag alone was not enough^ however^ to define the best operating con- 
dition. As a minimim consideration the effects of pressure recovery and 
additive drag were optimized for a selected engine to obtain the best operat- 
ing conditions for a given vehicle flight profile. The additive drag and 
total-pressure recovery were functions of the inlet mass flow and the cowl 
position. Positions for minimum additive drag were also those with low recov- 
ery as indicated in figure 20. The only realistic way of considering the best 
combination of recovery and additive drag was to select an engine with a known 
airflow schedule and optimize the thrust minus additive drag for a given 
flight profile. In this way the optimized set of curves in figure 20 was 
obtained. Because of the strong influence of pressure recovery on engine 
thrust^ optiimm performance occurs with other than minimum additive drag. 
Each engine-inlet combination requires a new optimization; hence^ more com- 
plete data and a sample computation for the results shown in figure 20 are 
presented in appendix B. The theoretical additive drag shown in figure 20 was 
computed with the method of characteristics and compares reasonably well with 
the experimental results. As mentioned in appendix B optimum performance at 
all transonic Mach numbers occurred with the cowl lip at or near 



12 



(x/R)iip = 3*50 while minimum additive drag occurred with (x/R)]_ip = 3.65. 
Thi^ reduction in translation of O.I5 x/r could result in a reduction of the 

inlet weight. 



CONCLUDING REMARKS 



A 20-inch capture diameter model of a mixed compression axisyrametric 
inlet system designed for high performance from ]^ = to 3.O has heen 
tested. Three relatively short subsonic diffusers have heen tested in combi- 
nation with virtually the same supersonic diffuser. The main conclusions to 
be drawn from these tests are that the supersonic portion of the inlet per- 
formed as predicted^ and that the main difficulty in achieving high perfor- 
mance lay in the elimination of flow separation in the throat and subsonic 
diffuser. Vortex generators located just downstream of the throat were effec- 
tive over the complete Mach number range in reducing the total pressure dis- 
tortion at the engine face of the shortest subsonic diffuser tested. Without 
vortex generators the distortions were high (about double that with genera- 
tors) and were considered unsatisfactory for most engines. The distortion 
with the generators was less than may be needed and suggests that even shorter 
subsonic diffusers are practical. 

The inlet with the shortest subsonic diffuser was about I.50 capLure 
diameters long measured from the cowl lip to the engine face. The supersonic 
portion was successfully designed with the aid of a computer program employing 
the method of characteristics. The subsonic diffuser problems were overcome 
with a design employing a linear Mach number variation from the beginning of 
the throat to the engine face. This variation allowed a low rate of initial 
expansion in the throat and avoided flow separation. 

The inlet showed good resistance to unstarting which might result from 
atmospheric disturbances sucn as gus'cs. GperfcLoiuii ixi bli^htly supercritical 
conditions with only a relatively small reduction in maximum pressure recovery 
was needed to maintain started conditions for local angles of attack ranging 
to 3-5°. 

Control of the boundary layer has been accomplished with four porous 
bleed areas. The boundary layer in the supersonic portion of the diffuser was 
effectively controlled by bleeding just ahead of two internal shock wave 
impingements- A distributed pattern of bleed in the throat region allowed an 
increase in bleed flow and engine-face recovery as the terminal shock-wave 
system moved into the throat. By altering the distribution of the bleed holes 
in the throat it should be possible to either lengthen or shorten to some 
extent the distance the terminal shock wave system can travel for a given 
level of performance. 

Ames Research Center 

National Aeronautics and Space Administration 

Moffett Field; Calif, j, 9^035^ Sept. 1, I967 
720-03-01-01-00-21 

13 



APPENDIX A 



PLOTTED DATA 



Figure 21.- Theoretical inlet mass -flow ratio^ a = 0*^. 

Figures 22(a) - 22(h) ^.- Supercritical performance^ I.50 D inlet with vortex 
generators^ a = 0^^ bleed exit settings A^ B, and C^ ly^o - 3*2 to 1.55. 

Figures 23(a) - 23(g) •^.- Supercritical perfoimance^ I.50 D inlet without vor- 
tex generators^ a = 0^, bleed exit settings A and C^ ]V^ = 3*0 to 1.55. 

Figure 2h.- Supercritical performance^ I.50 D inlet with vortex generators^ 
bleed exit setting B, ^ = 3-0, a - 0°, (VR)iip = 2.320, 2.330, 2.350, 
2.370, 2.^00. 

Figures 25(a) - 25(h).- Bleed zone mass flow, I.50 D inlet with vortex genera- 
tors, a = 0*^, bleed exit settings A, B, and C, jy^^ - 3*20 to 1.55. 

Figures 26(a) - 26(f).- Pitot pressure profiles, I.50 D inlet, bleed exit set- 
ting B, a = 0^, H=o = 2.75 to 1.55.^ 

Figures 27(a) - 27(d).- Bleed zone plenum chamber pressures, I.50 D inlet with 
vortex generators, (x/R)iip = 2.33O, M^ = 3-00, a = 0^, bleed exit settings 
A, B, C, and D. 

Figures 28(a) - 28(d).- Maximum bleed zone plenum chamber pressures, I.50 D 
inlet with vortex generators, a = 0^, bleed zones I, II, III, and IV. 

Figures 29(a-c) - 35(a-c).- Static pressure distribution, I.50 D inlet with 
vortex generators, bleed exit setting B, a = 0^, I^ - 3*20, 2.75 to 1.55* 

Figures 36(a) - 36(g).- Maximum performance at angle of attack, I.50 D inlet 
with vortex generators, M^^ = 3. 00 to 1.55- 

Figures 37(a) - 37(g).- Maximum performance at angle of attack, I.50 D inlet 
without vortex generators, Moo = 3-00 to 1.55. 

Figures 38(a) - 38(e).- Supercritical performance at angle of attack, I.50 D 
inlet with vortex generators, bleed exit setting B, N^o = 2.75 to 1.75 . 

Figures 39(a) - 39(i).- Transonic total-pressure recovery and additive drag, 
a - 0°, ly^ = 0.60 to 1.20. 



^Half-filled symbols on these figures indicate points for which tabulated 
data are presented. 

^y\^ - 3.00 data shown in section on Discussion only. 

11+ 



APPETOIX B 

METHOD OF DETERMINING THE OPTIMUM COMBINATION OF TRANSONIC 
ADDITIVE DRAG AND TOTAL -PRESSURE RECOVERY 



The transonic additive drag and total-pressure recovery were a function 
of the inlet mass flow and the cowl position. Conditions that yielded low 
additive drag generally yielded low recovery. The reverse was also true; 
therefore^ the tradeoff between drag and recovery was calculated for an appro- 
priate engine with an ass^omed flight profile to show an example of the optimiom 
combination of additive drag and pressure recovery. Data needed for optimiza- 
tion at Mach numbers 0.6 to 1.2 are presented in figure 39(a) ^ and an example 
of the computation procedure is outlined below for Mach number 0.6. 

From engine performance data^ values of thrust for 100-percent throttle 
setting were found at Mach number 0.6 at the altitude defined by the assumed 
flight profile shown in figure 4o(a). These values of thrust were corrected 
for the pressure recoveries for the range of inlet mass flow xn^/m shown in 
figure 39(3'). Thrust was converted to thrust coefficient Cjfrj^, and from Cy^ 
the corresponding additive drag coefficient Cd was subtracted. At this 
point the engine mass flow demand was checked to see if enough flow was avail- 
able from the inlet. Since there was ample inlet flow^ as shown in figure 20^ 
part was bypassed^ producing an additional drag penalty that was not included 
in the computations. Curves of C-^ - Cj]^ versus m^/m were determined for 
each cowl position (x/R)iip as shown in figure ^O(b). For the Mach number of 
this example the peak or optimum Cirj^ - CDq, occurred near ^/"^ ~ 0.355 with 
(x/R)]_ip = 3.50. Then CDa ^^^ Pt2/Ptoo ^^^ this point were plotted in fig- 
ure 20 as were the points for other transonic Mach numbers. For this particu- 
lar enp:ine -inlet combination the optim^um transonic operating points shown all 
occurred with the cowl lip near the x/R = 30^ position. 



15 



REFERENCES 



!• Sorensen^ Norman E.; and Smeltzer^ Donald B.: Study and Development of an 
Axisyrnmetric Supersonic Inlet. Presented at AIM Propulsion Joint 
Specialist Conference^ Colorado Springs^ Colorado^ June l^-l8^ I965. 

2. Sorensen^ Norman E.; Anderson^ Warren E.; Wong^ Norman D.; and Smeltzer^ 

Donald B.: Performance Summary of a Two -Dimensional and an Axisyrnmetric 
Supersonic Inlet System. NASA TM X-I302, I966. 

3. Sorensen^ Virginia L.: Computer Program for Calculating Flow Fields in 

Supersonic Inlets. NASA TN D-2897, I965. 

h. Kuehn^ Donald M. : Experimental Investigation of the Pressure Rise 

Required for the Incipient Separation of Turbulent Boundary Layers in 
Two -Dimensional Supersonic Flow. NASA NLEMO 1-21-59A^ 1959- 

5. Strike^ W. T.; and Rippy^ J. 0.: Influence of Suction on the Interaction 

of an Oblique Shock -with a Turbulent Boundary Layer at Mach Number 3» 
AEDC-TN-61-129^ Oct. 1961. 

6. Taylor^ Harlan D. : Summary Report on Vortex Generators. United Aircraft 

Corp. Department Report R-05280-9^ March 7^ 1950. 

7. SibulkiH; Merwin: Theoretical and Experimental Investigation of Additive 

Drag. NACA Rep. II87, 195^. 



16 



TABLE I.- INLET COORDINATES 



CENTERBODY 



COWL 



INITIAL 

1.75 D 
INLET 


MODIFIED 
1.75 D 
INLET 


1.50 D 
INLET 


X 

R 


r 
R 


X 

R 


r 
R 


X 

R 


r 
R 




















Straight linej 


Straight line| 


Straight line] 


3-300 


.730 


3.300 


.730 


3-300 


-730 


3-325 


.735 


3.325 


-735 


3-325 


-7355 


3-350 


.740 


3.350 


.7to 


3.350 


• 7to5 


3.375 


.71+5 


3.375 


.71+5 


3-375 


.7^5 


3. too 


.7k9 


3. too 


■ 7^9 


3. too 


-750 


3.1+25 


.753 


3.1+25 


-753 


3-1+25 


.751+ 


3-^50 


.757 


3.^50 


.757 


3- 1+50 


-7575 


3.i+75 


.760 


3.1+75 


.760 


3-1+75 


• 7615 


3.500 


.7^3 


3.500 


.763 


3-500 


-765 


3.525 


.766 


3.525 


.766 


3-525 


-7675 


3.550 


.7675 


3.550 


.7675 


3-550 


-770 


3.575 


.769 


3.575 


-769 


3-575 


• 772 


3.600 


.7705 


3.600 


-7705 


3. 600 


-773 


3.625 


.772 


3-625 


.772 


3-625 


-771+ 


3.650 


.772 


3.650 


• 772 


3.650 


-775 


3.675 


.7705 


3-675 


-7705 


3-675 


-771+ 


3.700 


.769 


3-700 


-769 


3.700 


-772 


3.725 


.767 


3-725 


-767 


3.725 


.768 


3.750 


.■j6k 


3-705 


-769 


3.750 


-765 


Straight line 


3-725 


-767 


Straight line| 


14-.050 1 .716 


Straight line] 


3.950 


.730 


'fiVtfT-infi -Pa.n<^ 


■5.000 


.6230 


I+.050 


.710 




5.100 


.611 


I+.I50 


.690 




5.200 


-598 


I+.25O 


.668 




5.300 


.58^ 


I+.35O 


.6^6 




5. too 


-570 


I+.I+50 


.623 




5-500 


-553 


I+.55O 


-599 




5.600 


-53^ 


I+.65O 


-571+ 




5-700 


-513 


I+.75O 


.5i+8 




5.800 




I+.85O 


.523 




5.900 


.U57 


I+.95O 


.1+98 




6.000 


.1+19 


5.050 


.1+725 




6.01+5 


.too 


5.150 


.^1+7 




Engine face 


5.250 


.1+235 




5-350 


.tol^ 




5-375 


.too 



Engine face 



INITIAL AND 

MODIFIED 
1.75 D INLET 


1.50 D 
INLET 


(-ti 


r 
R 


(f^. 


r 
R 





1.000 





1.000 


Straight line] 


Straight line 


.1+50 


1.000 


.1+50 


1.000 


.500 


.999 


.500 


-999 


.550 


.998 


.550 


-998 


.600 


.9975 


.600 


-9975 


.650 


■997 


.650 


-997 


.700 


.995 


.700 


.995 


.750 


.9925 


.750 


-9925 


.800 


.990 


.800 


-990 


.850 


.987 


.850 


.987 


.900 


.98U 


.900 


.98^ 


.950 


■ 979 


.950 


-979 


1.000 


■ 973 


1.000 


-973 


1.050 


.966 


1.050 


.966 


straight line | 


straight line | 


i.too 


.920 


1.700 


.875 


1.1+25 


.917 


1.800 


.862 


1.1+50 


.915 


1.900 


.81+9 


1.1+75 


.9125 


■ 2.000 


.836 


1.500 


.911 


2.100 


.821+ 


1.550 


.908 


2.200 


.812 


1.600 


.905 


2.300 


.802 


1.650 


.902 


2. too 


-792 


1.700 


.oyy 


2. 50c 


r-rOl. 


1.800 


.893 


2.600 


.778 


1.900 


.888 


2.700 


-775 


2.000 


.882 


2.800 


-776 


2.100 


.876 


2.850 


-778 


2.200 


.871 


2.900 


.782 


2.300 


.866 


2.950 


-790 


2. too 


.861 


3.000 


.802 


2.500 


.856 


3.050 


.815 


2.600 


-8525 


3.100 


.823 


2.700 


.81+8 


3.125 


.825 


2.800 


.81+5 


Engine face 


2.900 


.81+1 




3.000 


.838 




3.100 


-835 




3.200 


.833 




3.300 


.830 




3. too 


.828 




3.500 


.827 




3.600 


.826 




3.670 1 .825 1 





Engine face 



17 



TABLE II.- ENGIITE-FACE PRESSURE RECOVERY DATA, p^ /p^ 



The following include total pressure recoveries from 
the individual tubes which were moiinted at the engine- 
face. Other quantities of interest are also included. 
A sketch showing the location of each tube is shown 
below. 



Rake 1 




Engine-face pressure tube location looking downstream 



18 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, P-^^/Pt " Continued 
(a) 1.50 D inlet with vortex generators 



M„ = 3.20 



a = 0.0° 



VtJvt = 0-776 nihl/mco = 0.077 



"o/"'oo = 1-000 

^Pt2 - 0-i'^7 



Exit setting 



35.61 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 
0,807 


h 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0,803 


0.806 


0.783 


0.751 


0.729! 2 


0.809 


0.809 


0.805 


0.799 


0.76ii 


0.732 


3 


0.802 


0,819 


0.787 


0.75^ 


0.733 


0.72l| k 


0.771 


0.795 


0.811 


0.790 


0.769 


0.739 


5 


0,8i4 


0.789 


0.773 


0.714.7 


0.728 


0.717I 6 


0,831 


0.819 


0.798 


0,772 


0.748 


0.727 



K. = 3-20 



a 



O.O'^ 



Pts/Pt^ = Q*^^3 m^i/moo = 0>06t 



I°o/lDoo = 
^Pt2 =- 



l.OOO 



Exit setting =_ 



0.210 



P2/P00 



32.38 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


h 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.805 


0.770 


0.727 


0.677 


0,656 


0.653 


2 


0.780 


0.755 


0.731 


0.701 


0.676 


0.665 


3 


0.7hk 


0.76i+- 


0.776 


0.756 


0.730 


0.703 


1+ 


0.778 


0.760 


0.756 


0.710 


O.67U 


0.659 


5 


0.773 


0.75^ 


0.748 


0,696 


0.662 


0.657 6 


0,779 


0.776 


O.75U 


0.701 


0.668 


0.659 



Mco= 3.20 



a = 



0,0° 



Ptp/Pt^ = Q'648 mti/nJoo = Q*Q65 



J^lo/lDoo 
^Pt2 



1.000 



Exit setting 



= 0.298 



P2/P00 



28.22 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


4 


5 


6 


1 0.557 


0.558 


0.559 


0.565 


0.553 


0.5ii-l 


2 0.626 


0.671 


0.682 


0.669 


0.705 


0.693 


3 0.595 


0,61^8 


0.682 


0.692 


0.706 


0.657 


k 0.590 


0,632 


0,634 


0.635 


0.690 


0.676 


5 0,606 


0.627 


0.658 


0.675 


0.68i^ 


0.704 


6 0.595 


0.673 


0,734 


0,715 


0.720 


0.675 



M^ = 3.20 



a = 0.0° 



D3o/Hloo 



1.000 



Exit setting =_ 



P^VPt = 0.777 in>,T/m„= 0.069 Ap^_ = 


0.148 


P^P„= 35. 5i^ 




RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 
0.802 


4 
0.799 


5 


6 


1 


0,802 


0.808 


0.813 


0.783 


0.747 


0.728 


2 


0.800 


0,811 


0.765 


0.735 


3 


0,805 


0,822 


0.785 


0.752 


0.735 


0.721 


4 


0.770 


0.796 


0.814 


0.793 


0.775 


0.744 


5 


0,813 


0.792 


0.775 


0.749 


0.730 


0.718 


6 


0.833 


0.822 


0.796 


0,771 


0.750 


0.730 



19 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, Pt2/Pt " Continued 
(a) 1.50 '^ inlet with vortex generators 



Moo 



3.20 



a - 



0.0' 



Pt>t = Q'^30 m>.n/m^ = Q'Q6l 



^Pt2 



1.000 



B 



= 0.223 



Exit setting = 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO, 


TUBE NO. 1 


1 


2 


3 


k 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.809 


0.757 


0.689 


0.655 


O.6I16 


0.614-7 


2 


0.791 


0.797 


0.777 


0.71^2 


0.719 


0.690 


3 


0.777 


0.782 


0.753 


0.725 


0.707 


0.689 


k 


0.750 


0.760 


O.7I17 


0,714.0 


0.727 


0.703 


5 


0.767 


0.787 


0.783 


0.7ij-l 


0.711 


0.690 


6 


0.783 


0.7*^3 


0.712 


O.67I+ 


0.656 


0.652 



M^= 3-20 



a = 



0.0° 



mo/ir 



1.000 



Exit setting 



Pt 2/Pt^ = Q'^3^ ii>bl/™co = Q-Q60 Ap^ = 0-302 



P^/Poo =_26^30_ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


ii 




6 


1 


0,6ij-5 


0.605 


0.570 


0.565 


0.558 


0.558 


2 


0.582 


0.5^9 


0.531 


0,5214- 


0.521 


0.521 


3 


0,614-2 


0.665 


0.693 


0.690 


0.691^ 


0.678 


It 


0.6llt 


0.650 


0.651^ 


0,656 


0.696 


0.712 


5 


0,6lli 


0,61^1 


0.6^8 


0.657 


0.680 


0.678 


6 


0.690 


O.69I4- 


0.702 


0.688 


0.691 


0.680 



M„= 3.20 



a 



0.0' 



)/ni, 



0/"^oo 



1.000 



Exit setting 



Pt^/Pt^ =_0^770_ m^i/m^ = 0>06l ^p^ = 0-1^1 



Pa/Pa 



35.18 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO, 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.800 


0.808 


0.787 


o.7i]-8 


0.717 


0.709 


2 


0.802 


0.801^- 


0.796 


0.794 


0.763 


0.731 


3 


0.811 


0.821 


0.781 


O.^hh 


0.718 


0.712 


h 


0.767 


0.795 


0.815 


0.794 


0.772 


0.739 


5 


0.798 


0.785 


0.774 


0.756 


0.731 


0.717 


6 


0.821 


0.826 


0.780 


0.748 


0.7211 


0.716 



Moo- 3-20 



0.0° 



mo/] 



in„ 



1.000 



Ptp/Pt " Q'^30 in^^/m^= 0-056 Ap^^ 



0.186 



Exit setting 

Pp/Poo 



33.58 



RAKE 
NO. 

1 


TUBE NO. 


RAKE 
NO, 


TUBE NO. 


1 
0.761 


2 


3 


h 


5 


6 


1 


2 


3 


h 


5 


6 


0.765 


0.780 


0.760 


0.733 


0.705 


2 


0.786 


0.767 


O.7I4-7 


O.69I4- 


0.666 


0.658 


3 


0,778 


0.751 


0.726 


0.689 


0.661 


0.653 


\ 


Q-777 


0.789 


0.783 


0.762 


0.718 


0.677 


5 


0,786 


0.755 


0.716 


0.675 


0.655 


0.653 


6 


0.788 


0.780 


0.783 


0.729 


0.691+ 


0.671 



20 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p^ - Continued 
(a) 1.50 D inlet with vortex generators 



Moo = 3-20 



a 



0.0 



VtJ^t " Q'^^^ ni^i/mco - Q>Q35 



mo/in^ = 1-QQQ Exit setting = C 

^Pt2 - Q'302 p^/p^ « 26.70 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO, 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


V 


5 


6 


1 


0.657 


0.609 


0.577 


0.56V 


O.5V9 


O.5V7 


2 


0.589 


O.5VV 


0.532 


0.528 


0.528 


0.528 


3 


0.716 


0.715 


0.691 


0.709 


0.722 


0.68V 


V 


0.609 


0.621 


O.6V9 


0.675 


0.715 


0.709 


5 


0.638 


0.656 


0.678 


0.680 


0.67V 


0.665 


6 


0.70 V 


O.70V 


0.700 


0.691 


0.690 


0.678 



Mco= 3-00 



a 



0.0° 



nioAoo = 0.999 



Exit setting =_ 



Pt.7Pt,., = 0-915 m^i/m^= 0.129 



^Ptj 



= 0.060 



vjv^ = 32-18 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


V 


5 


6 


1 


2 


3 


It 


5 


6 


1 


0.898 


0.910 


0.910 


0.911 


0.902 


0.911 


2 


0.896 


0.916 


0.898 


0.916 


O.9I1I1 


O.9U0 


3 


0.927 


0.930 


0.932 


0.91V 


0.927 


0,909 


V 


0.888 


0.898 


0.896 


0.919 


0.930 


0.936 


5 


0.915 


0.909 


0.917 


0.916 


0.917 


0.901 


6 


0.93i^ 


0.927 


0.927 


0.909 


0.930 


o.89i; 



Mco= 3.00 



a = 



0.0° 



Pt2/Pt<„ = 0-878 Dibi/n 



0.092 



^Ptp = - 



0.999 



Exit setting 



0.069 



P2/P00 



31.59 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


k 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.853 


0.863 


0.85*^ 


0.868 


0.872 


0.866 


2 


0.859 


0.879 


0.858 


0.877 


0.89i+ 


0.905 


3 


0.897 


0.89i+ 


0.897 


0.873 


0.896 


0.873 


h 


O.8U7 


0.866 


0.858 


0.881 


0.899 


0.908 


5 


0.873 


0.867 


0.866 


0.868 


0.873 


0.858 


6 


0.902 


0.896 


0.904 


0.888 


0.908 


0.87!^ 



Moo = 3-00 



a = 0.0° 



mo/iDco = 0.999 



Exit setting =_ 



p. /p. = 0.806 nw^/m^= 0.077 Ap = 0.110 



Pg/p^- 27-70 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.822 


0.781 


0.765 


0.781 


0.812 


0.801+ 


2 


0.806 


0.797 


0.764 


0.788 


0.852 


0.823 


3 


0.850 


0.812 


0.803 


0.798 


0.821 


0.803 


1+ 


0.799 


0.812 


0.773 


0.778 


0.819 


0.844 


5 


0.827 


0.800 


0.785 


0.788 


0.781 


0.780 


6 


0.836 


0.8lit 


0.825 


0.812 


0.824 


0.839 



21 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p^ - Continued 
(a) 1.50 D inlet with vortex generators 



Mco = 3-00 



a 



0.0° 



I°o/"^oo = 



0.999 



vtjvt = Q'9io m^,/m^= 0.109 Ap. =, 



0.062 



Exit setting 
P2/P00 



31.76 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


h 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.903 


0.910 


0.915 


0.905 


0.896 


0.901 


2 


0.892 


0.909 


0.892 


0.922 


0.936 


0.932 


3 


0.928 


0.921 


0.927 


0.909 


0.926 


0.902 


h 


0.884 


0.892 


0.888 


0.910 


0.916 


0.915 


5 


0.916 


0.911 


0.918 


0.906 


0.905 


0.885 


6 


0.931 


0.921 


0.920 


0.902 


0.918 


0.880 



M^= 3.00 



a = 



0.0' 



Vtjvt^ = Q-885 m^Jm^ = 0.086 



mo/ra, 
^Pt2 = 



0.999 



= 0.087 



Exit setting = 5__ 

vjv^ = 30-71 



RAKE 
NO. 

1 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


_ 2 


3 


k 


5 


6 


1 


2 


3 


k 


5 


6 

0.909 


0.87ij- 


0.87^^ 


0.867 


0.873 


0.868 


0.86U 


2 


0.868 


0.88U 


0.865 


0.890 


0.900 


3 


0.910 


0.903 


0.902 


O.87I+ 


0.898 


0.880 


k 


0.860 


0.878 


0.865 


0.89^+ 


0.901 


0.899 


5 


0.89^^ 


0.879 


0.881+ 


0.870 


0.870 


0.8I1U 


6 


0.921 


0.909 


0.906 


0.888 


0.908 


0.881 



M„= 3.00 



a = 



0.0' 



Ptp/Pt = Q-8i^ iQhi^oo- Q'QTi 



^Pt2 = - 



0.999 



0.108 



Exit setting 



P^/Po 



27.87 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


h 


5 


6 


1 


2 


3 


h 


r 

5 


6 


1 


0.842 


0.796 


0.780 


0.793 


0.806 


0.799 


2 


0.818 


0.809 


0.777 


0.809 


0.863 


0.819 


3 


0.865 


0.820 


0.811 


0.806 


0.826 


0.805 


h 


0.811 


0.826 


O.78I+ 


0.799 


0.827 


0.842 


5 


0.848 


0.808 


0.793 


0.793 


0.785 


0.779 


6 


0.856 


O.82I+ 


0.832 


0.810 


0.827 


0.833 



M = 3.00 



a = 0.0° 



mo/moo = 0.999 



Exit setting =_ 



PtA = °-9°g m^i/m^ = 0.098 



•t2 



= 0.068 



Ps/Poo ' 



31.43 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


k 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.896 


0.902 


0.90!; 


0.895 


0.885 


0.892 


2 


0.888 


0.902 


0.889 


0.920 


0.93^ 


0.921 


3 


0.92^]- 


0.918 


0.921 


0.897 


0.913 


0.890 


h 


0.876 


0.888 


0.881 


0.903 


0.911 


0.909 


5 


0.909 


0.905 


0.909 


0.899 


0.896 


0.873 


6 


0.930 


0.917 


0.911 


0.893 


0.908 


0.873 



22 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, Pt2/Pt " Continued 
(a) 1.50 D inlet with vortex generators 



^00 = 3>oo 



a = 



0.0° 



Ptp/Pt " Q'Q90 iQbiAcc = Q>Q82 



°io/"^oo = Q'999 Exit setting = C 
APt^ - Q'Q9^ vjv^ - 30-87 



RAKE 
NO. 


TUBE NO. 


RAKE 


TUBE NO. 


1 


2 


3 


h 


5 
0.865 


6 


NO. 


1 


2 


3 


k 


5 


6 


J- 


0.887 


0.88)! 


0.877 


O.87U 


0.858 


2 


0.879 


0.894 


0.873 


0.900 


0.908 


0.903 


3 


0.923 


0.906 


O.90U 


0.879 


0.900 


0.876 


k 


0.870 


0.885 


0.879 


0.899 


0.902 


0.887 


5 


O.9OU 


0.887 


0.893 


0.87^+ 


0.868 


0.849 


6 


0.933 


0.920 


0.910 


0.887 


0.906 


0.875 



Moo = 3-00 



a = 



0.0" 



/inco= 0.999 



Ptp/Pt = Q'820 n>bi/moo =_0^065_ 



IDq 



^Ptp = . 



Exit setting = C_ 



0.108 



P^/Pco 



28.11 



RAXE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


\ 


5 


6 


1 


2 


3 


It 


5 


6 


1 


0.857 


o.80ii 


0.789 


0-797 


0.807 


0.802 


2 


0.827 


0.817 


0.785 


0.813 


0.857 


0.834 


3 


0.87^ 


0.82U 


0.812 


0.809 


0.832 


0.811 


k 


0.821 


0.835 


0.791 


0.803 


0.826 


0.848 


5 


0.858 


o.SU 


0.791+ 


0.795 


0.793 


0.790 


6 


0.867 


0.829 


0.832 


0.816 


0.828 


0.843 



M«>= g-'^^ 



a = 



0.0^ 



/iD^= 0.938 



n^o/^oo 



Exit setting 



Pt2/Pt<„ = 0-91^ '^l/n'oo = 0-133 Ap. = 



0.110 



P2/P0O 



21.59 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 






1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.936 


0.901 


0.922 


0.907 


0.926 


0.875 


2 


0.912 


0.932 


0.915 


0.937 


0.924 


0.881 


3 


0.957 


0.938 


0.918 


0.898 


0.923 


0.857 


4 


0.901 


0.915 


0.909 


0.906 


0.916 


0.927 


5 


0.942 


0.910 


0.933 


0.891 


0.900 


0.879 


6 


0.954 


0.935 


0.920 


0.912 


0.925 


0.857 



Moo 



2.75 



a = 



0.0 



mo/moo = 0.938 



Exit setting 



PtVPt = Q-9Q^ mbi/m^= 0-119 



^Pt.= 



= 0.081 



Pa/Pcc ^ 



2\.k2 



RAKE 

NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


h 


5 

0.921 


6 

0.891 


1 


0.921 


0.887 


0.905 


0.899 


0.927 


0.882 


2 


0.885 


0.916 


0.887 


0.914 


3 


0.935 


0.919 


0.919 


0.892 


0.920 


0.863 


k 


0.879 


0.903 


0.886 


0.902 


0.909 


0.930 


5 


0.923 


0.892 


0.907 


0.890 


0.901 


0.865 


6 


0.930 


0.915 


0.920 


0.91U 


0.920 


0.862 



23 



TABLE II.- ENGINE-F/VCE PRESSURE RECOVERY DATA, p. /p. - Continued 
(a) 1.50 D inlet with vortex generators 



M^= 2.75 



0.0' 



nio/^oo = 



Pts/Pt = 0-855 mti/moo - 0.097 Ap^^ = 0-105 



0-938 Exit setting = _± 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 

2 


TUBE NO. \ 


1 


2 


3 


k 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.889 


0.838 


0.827 


0.836 


0.869 


O.8I+I1 


O.8I12 


0.857 


0.818 


0.81+1 


0.894 


0.838 


3 


0.902 


0.87i+ 


0.8^8 


0.838 


0.875 


0.826 


1^ 


0.837 


0.862 


0.820 


O.83U 


0.853 


0.908 


5 


0.889 


0.837 


0.834 


0.836 


0.83i^ 


0.8h5 


6 0.906 


0.875 


0.889 


0.854 


0.874 


0.849 



Mco= 2-7 5 



a = 0.0° 



Pt.VPt = 0-913 nj^i/ii 



0.120 



mo/moo = 
^Ptp = 



0.938 



Exit setting = B 



0.123 



P^/P^ - 21-38 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.951 


0.907 


0.926 


0.898 


0.914 


0.861 


2 


0.921 


0.932 


0.921 


0.943 


0.918 


0.878 


3 


0.962 


0.949 


0.915 


0.889 


0.910 


0.854 


k 


0.903 


0.916 


0.915 


0.904 


0.914 


0.925 


5 


0.950 


0.914 


0.936 


0.884 


0.895 


0.859 


6 


0.963 


0.947 


0.916 


0.907 


0.915 


0.851 



Ko = 2-T5 



Of = 0.0" 



P,.7p, = 0.902 i^ti/n 



0.104 



^Pt2 



Exit setting = b 



= 0.109 



P^/Poo 



21.13 



RAKE 

NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.930 


0.891 


0.910 


0.887 


0.918 


0.866 


2 


0.894 


0.915 


0.890 


0.922 


0.914 


0.884 


3 


0.947 


0.917 


0.911 


0.881 


0.909 


0.849 


4 


0.883 


0.901 


0.885 


0.897 


0.902 


0.935 


5 


0.931 


0.895 


0.911 


0.884 


0.898 


0.859 


6 


0.946 


0.918 


0.907 


0.902 


0.905 


0.877 



Meo = 2.75 



a = 0.0' 



^tM= °-Q^3 m^iA 



mo/nioo = 0-938 
0.091 ^P+-_ = 0.098 



Exit setting = B 



■t2 



Pp/P^- 20-31 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.907 


0.857 


0.852 


0.854 


0.887 


0.850 


2 


0.859 


0.873 


0.843 


0.879 


0.896 


0.878 


3 


0.913 


0.888 


0.882 


0.848 


0.873 


0.853 


4 


0.853 


0.868 


0.838 


0.864 


0.880 


0.921 


5 


0.900 


0.855 


0.856 


0.854 


0.859 


0.847 


6 


0.924 


0.892 


0.895 


0.871 


0.887 


0.875 



2k 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p. - Continued 
(a) 1,50 D inlet with vortex generators 



M^= 2.75 



a 



0.0° 



°o/^ 



m^/m^ = 



0.938 



WPt^= Q-9Q9 m^i/ 



ffion = 



O.lOli 



^Ptp =. 



0.121 



Exit setting = 

Ps/Pcc " 



21.08 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


k 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.9^7 


0.902 


0.925 


0.887 


0.906 


0.853 


2 


0.889 


0.909 


0.886 


0.91+6 


0.957 


0.856 


3 


O.9I1I 


0.936 


0.9^+3 


0.892 


0.928 


0.865 h 


0.895 


0.908 


0.907 


0.903 


0.908 


0.921 


5 


0.946 


0.908 


0.93^ 


0.878 


0.885 


0.856 6 


0.953 


0.937 


0.937 


O.90I1 


0.930 


0.847 



Moo 



2.75 



a 



0.0' 



Pt.o/Pt, = 0-8T9 m^i/i 



IDrv. = 



^o/nio, 

Q-Q87 Ap^. 



0.938 



Exit setting 



= C 



0.112 



P^/Pc 



20.25 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 

=■-.. ^ 


h 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.918 


0.867 


0.866 


0.853 


0.882 


0.838 


2 


0.857 


0.882 


0.851 




0.900 


0.930 


0.832 


3 


0.912 


0.906 


0.905 


0.854 


0.882 


0.849 


4 


0.865 


0.876 


0.852 


0.884 


0.895 


0.907 


5 


0.907 


0.868 


0.873 


0.851 


0.851 


0.837 


6 


0.929 


0.905 


0.924 


0.877 


0.893 


0.857 



Moo= 2-?Q 



a = 



0.0" 



i^o/nioo = 0.851 



Pto/Pt, = Q'930 mb> 



0.130 



^Ptp = 



0.076 



Exit setting 
Po/P^ 



111. 76 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.937 


0.906 


0.932 


0.909 


0.943 


0.917 


2 


0.904 


0.932 


0.911 


0.949 


0.950 


0.926 


3 


0.949 


0.9^3 


0.952 


0.920 


0.930 


0.889 


4 


0.915 


0.911 


0.910 


0.947 


0.944 


0.960 


5 


0.937 


0.908 


0.939 


0.923 


0.925 


0.906 


6 


0.949 


0.944 


0.946 


0.943 


0.948 


0.907 



M^= 2.50 



a = 0.0° 



mo/n 



0.851 



Exit setting 



= A 



p^7Pt = 0-901 r:^,/m^= 0.104 Ap = 


0.10£ 


] 


vjv^- 1^-15 


T^2 i-oo 2 




RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 

0.939 


1 


0.878 


0.863 


0.879 


0.907 


0.916 


0.898 


2 


0.865 


0.877 


0.872 


0.920 


0.922 


3 


0.894 


0.900 


0.919 


0.909 


0.905 


0.908 


4 


0.866 


0.869 


0.875 


0.923 


0.928 


0.961 


5 


0.890 


0.872 


0.887 


0.916 


0.894 


0.886 


6 


0.903 


0.904 


0.923 


0.930 


0.937 


0.917 



25 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, P^^/Pt " Continued 
(a) 1.50 D inlet vith vortex generators 



M = 



2.50 



a 



0.0^ 



^q/'^oo 



0.851 



5t>t^=llM_ 



m^l/m^ - 0-093 Ap. - O.IU5 



Exit setting 

P^/Pco 



13.07 



RAKE 
NO. 

1 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


h 


5 


6 


1 


2 


3 


k 


5 


6 


0.853 


0.813 


0.831 


0.8JiO 


0.851 


0.832 


2 


O.83U 


o.8i+o 


0.830 


0.871 


0.856 


0.822 


3 


0.877 


0.888 


0.916 


0.840 


0.816 


0.809 


k 


0.829 


0.845 


0.823 


0.87U 


0.857 


0.875 


5 


0.871 


0.833 


0.851 


0.853 


0.807 


0.795 


6 


0.863 


0.868 


0.919 


0.883 


0.848 


0.863 



M^- 2.50 



a 



0.0" 



Pto/Pt = 0-929 rn^i/moo = 0.108 



nio/m^ 



^Pt, 



0.851 



0.085 



Exit setting = B_ 



P^/p^ = 14.67 



RAKE 
NO. 


TUBE NO. 1 RAKE 


TUBE NO. 


1 


2 


3 


h 


5 




1 


2 


3 


h 


5 


6 


1 


O.9IT 


0.89^ 


0.918 


0.926 


O.9U1 


0.925! 2 


0.888 


0.914 


0.889 


0.952 


0.96] 


0.961 


3 


0.937 


0.936 


0.962 


0.933 


0.927 


0.920 h 


0.895 


0.897 


0.897 


0.958 


0.951 


0.967 


5 


0.931 


0.900 


0.928 


0.933 


0.921 


0.907 6 


0.9^1 


O.9UO 


0.96U 


0.91+8 


0.963 


0.9^U 



Ko 



2.50 



a 



0.0° 



Ptp/Pt = Q'Q95 m^i/m^^ 0.091 



"^0/^00 = 
^Ptp = - 



0.851 



0.118 



Exit setting 



P2/P00 



13.93 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.858 


0.853 


0.877 


0.899 


0.927 


0.902 


2 


0.850 


0.850 


0.856 


0.910 


0.943 


0.938 


3 


0.866 


0.883 


0.931 


0.912 


0.897 


0.906 


4 


0.852 


0.849 


0.856 


0.915 


0.938 


0.955 


5 


0.875 


0.863 


0.880 


0.912 


0.896 


0.886 


6 


0.879 


0.889 


0.925 


0.933 


0.937 


0.931 



M = 2.50 



a = 



0.0° 



Pt> 



2^^t^ 



■829 in^i/m^= 0.084 



21o/nico = 



0.851 Exit setting B 

0.118 TD /d = 12.50 



Ps/Pc^ 



RAKE 

NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.836 


0.791 


0.819 


0.807 


0.815 


0.806 


2 


0.790 


0.811 


0.802 


0.863 


0.847 


0.835 


3 


0.849 


0.848 


0.883 


0.806 


0.806 


0.822 


4 


0.791 


0.828 


0.804 


0.883 


0.840 


0.868 


5 


0.854 


0.809 


0.845 


0.798 


0.798 


0.803 


6 


0.868 


0.862 
— 1 


0.888 


0.838 


0.811 


0.838 



26 



TAELE II.- ENGINE-FACE PRESSURE RECOVERY DATA, Vtjvt " Continued 
(a) 1.50 D inlet vith vortex generators 



M„= 2.50 



a = 



0.0° 



P.7p. = Q-926 m^i/m. 



0.095 



^Pt2 



0.851 



0.083 



Exit setting = 

Pz/Pcx, " 



14.56 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


1+ 
0.915 


5 
0.933 


6 
0.915 


1 


2 


3 


h 


5 


6 


1 


0.913 


0.895 


0.923 


2 


0.888 


0.910 


0.888 


0.950 


0.959 


0.960 


3 0.932 


0.935 


0.962 


0.932 


0.920 


0.921 


k- 0.891 


0.896 


0.900 


0.958 


0.951 


0.961 


5 0.927 


0.900 


0.930 


0.930 


0.913 


0.897 


6 0.939 


0.940 


0.964 


0.943 


0.961 


0.891 



H.= g-^o 



a = 



0.0° 



Pto/Pt,= Q-89g ii>bi/in^=_^.:078 



^o/nioo = 
^Pt2 = - 



0.851 



Exit setting =_ 



0.118 



P^/Pco = 13.85 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


4 




6 


1 


2 


3 


4 


5 


6 


1 


0.850 


0.851 


0.880 


0.894 


0.917 


0.897 


2 


0.842 


0.851 


0.869 


0.923 


0.939 


0.932 


3 


0.850 


0.879 


0.923 


0.907 


0.888 


0.909 


4 


0.849 


0.850 


0.868 


0.918 


0.931 


O.9U7 


5 


0.864 


0.856 


0.882 


0.912 


0.892 


0.883 


6 


0.869 


0.882 


0.919 


0.933 


0.934 


0.930 



K>= g-^o 



a = 



0.0° 



noAo 



0.851 



Pt^/Pteo " Q'Q^3 mbl/°^oo = 0.072 



APtp = O.1I18 



Exit setting 

P^/Poo 



12.84 



RAKE 
NO. 


TUBE 


NO. 




RAKE 
NO. 


1 

TUBE NO. 1 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.826 


0.800 


0.815 


0.831 


0.858 


0.840 


2 0.802 


0.821 


0.812 


0.874 


0.866 


0.874 


3 


0.847 


0.846 


0.899 


0.832 


0.822 


0.851 


4 


0.792 


0.823 


0.805 


0.873 


0.875 


0.918 


5 


0.843 


0.8l4 


0.840 


0.822 


0.829 


0.840 


6 


0.848 


0.849 


0.901 


0.856 


0.841 


0.877 



Moo 



2.25 



a = 



0.0° 



mo/moo = 0.738 



Ptp/Pt =_2^952_ mv.n/m^=: 0.133 



Ap. = 0.0i|8 
^2 



Exit setting - A 

P2/Pc„"=_10i26_ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


4 


5 


6 


1 


2 


3 

0.941 


4 


5 


6 


1 


0.933 


0.935 


0.953 


0.964 


0.965 


0.951 


2 


0.931 


0.937 


0.968 


0.965 


0.963 


3 


0.939 


0.949 


0.962 


0.965 


0.960 


0.941 


4 


0.928 


0.928 


0.943 


0.959 


0.966 


0.974 


5 0.940 


0.932 


0.953 


0.945 


0.952 


0.945 


6 


0.949 


0.953 


0.963 


0.967 


0.969 


0.968 



27 



TABLE 11.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p^ - Continued 
(a) 1.50 D inlet with vortex generators 



Moo = g-2^ 



a 



0.0' 



Ptp/Pt = Q-930 m^i/rr 



0.108 



°^n/^co = 



^Pt, 



0.738 



0.093 



Exit setting = ^ 



90 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 

2 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.891 


0.913 


0.938 


0.954 


0.957 


0.939 


0.887 


0.891 


0.905 


0.945 


0.958 


0.966 


3 


0.884 


0.898 


0.922 


0.949 


0.942 


0.951 


4 


0.886 


0.896 


0.920 


0.944 


0.962 


0.971 


5 


0.910 


0.905 


0.922 


0.943 


0.941 


0.937 


6 


0.909 


0.924 


0.947 


0.962 


0.965 


0.964 



Moo = g-23 



a 



0.0" 



Ptp/Pt - Q-QQ9 rt^^/mpo- Q>QT8 



mo/nioo = 



Apt, 



0.738 



Exit setting = A_ 



0.093 



P^/Poo 



9.1^ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 

— 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.854 


0.893 


0.920 


0.899 


0.896 


0.871 


2 


0.845 


0.859 


0.878 


0.896 


0.881 


0.888 


3 


0.853 


0.879 


0.897 


0.896 


0.877 


0.887 


4 


0.861 


0.893 


0.921 


0.922 


0.921 


0.915 


5 


0.864 


0.867 


0.884 


0.892 


0.884 


0.863 


6 


0.874 


0.892 


0.916 


0.927 


0.921 


0.912 



Moo= 2-25 



a = 0.0° 



Pt7Pt = 0.9^7 n^,/m^= 0.109 



nio/lOoo 
^Pt2 = 



0.738 



Exit setting 



_ . 060 



P2/P00 



10.09 



RAKE 
NO. 


TUBE NO. 


RAKE 


TUBE NO. 


1 


2 


3 


4 


5 


6 


NO. 


1 


2 


3 


4 


5 


6 


1 


0.923 


0.926 


0.948 


0.960 


0.957 


0.946 


2 


0.921 


0.924 


0.936 


0.967 


0.963 


0.962 


3 


0.930 


0.943 


0.960 


0.963 


0.954 


0.939 


4 


0.918 


0.917 


0.938 


0.956 


0.964 


0.974 


5 


0.932 


0.923 


0.951 


0.942 


0.940 


0.937 


6 


0.945 


0.952 


0.963 


0.967 


0.968 


0.967 



M„= 2.25 



a = 0.0° 



mo/mco = 0-738 



Exit setting 



_ B 



v^ Jv^ = 0-933 mt.i/m^= O.092 



Ai 



•t2 



0.098 



P2/P00 



9-83 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.893 


0.910 


0.936 


0.957 


0.951 


0.937 


2 


0.886 


0.895 


0.920 


0.958 


0.959 


0.969 


3 


0.880 


0.901 


0.933 


0.955 


0.935 


0.956 


4 


0.886 


0.897 


0.923 


0.952 


0.967 


0.971 


5 


0.912 


0.905 


0.933 


0.943 


0.933 


0.926 


6 


0.921 


0.930 


0.957 


0.966 


0.966 


0.959 



28 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p^. - Continued 
(a) 1.50 D inlet vith vortex generators 



M„o= g-2^ 



a = 



0.0° 



n.o/m^ = 0-738 



Pt^/Pt = Q-90g if^i/moo^ 0-071 Ap^^ 



0.098 



Exit setting 
Pa/Poo 



9-30 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.857 


0.893 


0.927 


0.918 


0.913 


0.893 


2 


0.855 


0.867 


0.890 


0.914 


0.900 


0.915 


3 


0.855 


0.88i^ 


0.907 


0.915 


0.887 


0.912 


1; 


0.863 


0.899 


0.928 


0.91+0 


o.9iio 


0.935 


5 


0.876 


0.877 


0.89ii 


0.911 


0.901 


0.887 


6 


0.883 


0.903 


0.922 


O.9U3 


0.937 


0.937 



Moo = _2:25_ 



a 



0.0^ 



/m„ = 0.738 



mo/moo 



Exit setting = C_ 



Pt.VPt.^ = 0-9^^ n>hi/moo = 0.095 Ap^ = 0.067 



Pa/Pcc = 10-01 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


h 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.917 


0.923 


0.947 


0.960 


0.952 


0.942 2 


0.912 


0.916 


0.937 


0.962 


0.966 


0.972 


3 


0.921 


0.93i^ 


0.953 


0.969 


0.945 


0.952 


4 


0.915 


0.913 


0.936 


0.964 


0.972 


0.975 


5 


0.93it 


0.922 


0.951 


0.940 


0.930 


0.925 


6 


0.946 


0.952 


0.963 


0.967 


0.967 


0.965 



Moo 



2.25 



a 



0.0 



mn/m 



O/^cc 



0.738 



Exit setting 



Pt.7Pt.__ = 0-933 m>.i/n.^= 0-083 Ap^, 



0.096 



P2/P00 



1 1 

RAKE 
NO. 


1 

TUBE NO. 


1 

HAKJS 
NO. 


1 

TUiii!; wu. 1 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0,894 


0.911 


0.935 


0.956 


0.946 


0.935 


2 


0.885 


0.897 


0.927 


0.961 


0.962 


0.970 


3 


0.882 


0.908 


0.935 


0.963 


0.926 


0.959 


4 


0.887 


0.901 


0.923 


0.951 


0.969 


0.972 


5 


0.910 


0.906 


0.935 


0.941 


0.929 


0.918 


6 


0.923 


0.93i+ 


0.958 


0.965 


0.963 


0.955 



^= g-g^ 



a = 0.0' 



mo/iHoo = 0-738 Exit setting 



PtVPt = Q-892 °^i/m^= 0-060 

^2 '^cr 



-2' "X-oo 



Ap^ = 0.090 

t2 



p /p ^ 9-06 



RAKE 
NO. 

1 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 
0.847 


2 
0.893 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 
0.906 


0.919 


0.903 


0.886 


0.859 


2 


0.847 


0.855 


0.871 


0.910 


0.891 


3 


0.870 


0.889 


0.907 


0.910 


0.875 


0.899 


4 


0.865 


0.895 


0.927 


0.916 


0.915 


0.915 


5 


0.871 


0.865 


0.896 


0.895 


0.873 


0.857 


6 


0.886 


0.908 


0.920 


0.926 


0.920 


0.908 



29 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^^/^t " Continued 
(a) 1.50 D inlet vith Vortex generators 



^00 = g-QQ 



a = 



0.0' 



°o/^ 



in^/in_ = 



0.625 



Pt>t ^ Q-9^Q m^i/m^^ 0-1^3 Ap,^=. 



o.oi^3 



Exit setting 

Ps/Pco 



7.01 



RAKE 
NO. 


TUBE NO. J 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.937 


0.9^+2 


0.958 


0.975 


0.970 


0.961 


2 


0.936 


0.938 


0.9^+6 


0.964 


0.973 


0.974 


3 


0.9^5 


0.951 


0.961 


0.975 


0.937 


0.957 


h 


0.938 


0.938 


0.957 


0.971 


0.977 


0.977 


5 


0.952 


O.9I1I+ 


0.965 


0.956 


0.955 


0.960 


6 


0.953 


0.958 


0.972 


0.97i+ 


0.978 


0.977 



Mco = 



2.00 



a 



0,0' 



n^o 



/n:^= 0^625 



Exit setting 



pt 



Vp. = °-935 °>b>c. = 0-^0^ Ap, =, 



0.086 



/p = 6.71 



2' ^00 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.898 


0.914 


0.938 


0.952 


0.942 


0.932 


2 


0.889 


0.896 


0.912 


0.938 


0.954 


0.961 


3 


0.892 


0.907 


0.933 


0.960 


0.938 


0.952 


4 


0.889 


0.908 


0.933 


0.961 


0.969 


0.957 


5 


0.917 


0.922 


0.949 


0.944 


0.942 


0.944 


6 


0.917 


0.935 


0.960 


0.967 


0.960 


0.959 



Mcc = 



2.00 



a = 0.0^ 



mo/ni^ = 0.625 



Exit setting = A 



Pt2/Pt„ 



mv.n/m^ = 0.085 ^^ = 0.112 



P2/P00 



6.21 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.845 


0.866 


0.891 


0.914 


0.915 


0.896 


2 


0.835 


0.852 


0.875 


0.896 


0.911 


0.905 


3 


0.834 


0.852 


0.872 


0.899 


0.902 


0.905 


4 


0.840 


0.853 


0.869 


0.903 


0.918 


0.928 


5 


0.850 


0.865 


0.883 


0.903 


0.923 


0.923 


6 


0.850 


0.867 


0.885 


0.918 


0.933 


0.933 



Moo= 2-00 



a - 



0.0" 



mo/mo 



0.625 



^2 f^oo 



mbi/m<„ = 0-10^ 



•t2 



= 0.051 



Exit setting = B 

P^/P^- 6.80 



RAKE 
NO. 


TUBE NO. 1 


RAKE 
NO. 


TUBE NO. 


1 


2 
0.938 


3 
0.959 


4 


5 


6 


1 
0.929 


2 


3 


4 
0.966 


5 


6 


1 


0.934 


0.975 


0.957 


0.954 


2 


0.929 


0.945 


0.975 


0.977 


3 


0.937 


0.947 


0.961 


0.977 


0.931 


0.964 


4 


0.935 


0.933 


0.958 


0.973 


0.976 


0.976 


5 


0.950 


o.9i^3 


0.967 


0.955 


0.9^^3 


0.942 


6 


0.955 


0.961 


0.972 


0.975 


0.975 


0.978 



30 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, Pts/^t " Continued 
(a) 1.50 ^ inlet with vortex generators 



Moo = 



2.00 



a 



0.0° 



m^U^ = 0.62^ Exit setting = B_ 



Ptp/Pt " Q'9^3 iD>.iAco = 0-09^ Ap^ = 0.0^^ 



Ps/pcx 



6.72 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


k 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.919 


0.932 


0.946 


0.955 


0.9i+6 


0.930 


2 


0.912 


0.914 


0.925 


0.960 


0.955 


0.956 


3 


0.919 


0.932 


0.955 


0.958 


0.936 


0.951 


h 0.924 


0.924 


0.9it5 


0.954 


0.963 


0.960 


5 


0.930 


0.928 


0.952 


0.9^1 


0.9^+4 


0.948 


6 0.914.3 


0.950 


0.956 


0.957 


0.963 


0.964 



Moo = 



2.00 



a = 0.0' 



mo/m„ = 0.62^ 



Exit setting = B_ 



Pt2/Pt„=_^:9o;L ">hi/i°oo= 0-QT9 Ap. =. 



0.120 



P2/P00 



6.38 



RAKE 
NO. 


TUBE NO. 


RAKE 


TUBE NO. 


1 


2 


3 


4 


5 


6 


NO. 


1 


2 


3 


4 


5 


6 


1 


0.863 


0.882 


0.902 


0.933 


0.939 


0.928 2 0.855 


0.869 


0.889 


0.912 


0.935 


0.943 


3 


0.856 


0.869 


0.884 


0.918 


0.928 


0.935 ^ 0.863 


0.872 


0.896 


0.911 


0.933 


0.964 


5 I0.876 


0.885 


0.905 


0.925 


0.932 


0.936 6 0.875 


0.889 


0.911 


0.930 


0.947 


0.964 



Moo= 2-00 



a = 0.0° 



Do/lDo 



0.625 



Exit setting 



Ptg/Pt = 0-955 m>,i/m^ = 0.090 Atd^ = 0.057 



P2/P00 



6.83 



RAKE 
NO. 


TUBE NO. 


RAKE 

NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.931 


0.934 


0.959 


0.974 


0.949 


0.947 


2 


0.923 


0.926 


0.944 


0.973 


0.977 


0.978 


3 


0.930 


0.944 


0.963 


0.977 


0.944 


0.974 


4 


0.931 


0.930 


0.957 


0.974 


0.975 


0.971 


5 


0.948 


0.937 


0.966 


0.954 


0.936 


0.932 


6 


o.95i^ 


0.961 


0.972 


0.974 


0.972 


0.975 



M_ = 



2.00 



a = 



0.0° 



mo/moo = 0-6^5 



Exit setting = 2_. 



p^^ /v^ = 0.936 mbi/m^= 0.079 Ap^ = 0.071 pA 


= 6 


.61 




RAKE 
NO. 

1 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 
0.957 


5 


6 


0.902 


0.928 


0.9^^ 


0.950 


0.936 


0,922 


2 


0.894 


0,901 


0.927 


0.952 


0.953 


3 


0.893 


0.911 


0.937 


0.950 


0.930 


0.941 


4 


0.907 


0.920 


0.951 


0.956 


0.957 


0.957 


5 |0.924 


0.925 


0.9^9 


0.938 


0.932 


0.925 


6 


0.933 


0.949 


0.958 


0.958 


0.958 


0.960 



31 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p^ - Continued 
(a) 1.50 D inlet vith vortex generators 



M = 2.00 



a = 



0.0° 



no/3 



m^/m^ = 



0.625 



Pt./p. =-^:9o^ -bl/: 



m^= Q-Q^^ Ap^. 



0.125 



Exit setting = 
Pg/Pco =■ 



6.27 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 

2 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 

0.869 


3 


h 


5 


6 


1 


0.85i)- 


0.876 


0.895 


0.925 


0.932 


0.922 


O.8I17 


0.889 


0.915 


0.931 


0.91+0 


3 


0.8lt5 


0.860 


0.881 


0.912 


0.919 


0.928 


1^ 


0,852 


0.866 


0.890 


0.913 


0.937 


0.953 


5 


0.866 


3.888 


0.907 


0.916 


0.928 


0.931 


6 


0.865 


0.881 


0.902 


0.925 


0,9118 


0.958 



M^ = ^^75. 



a 



0.0° 



mo/m«, = 0-^21 



Exit setting 



Pt2/Pt<„ = 0-9^^ n>bl/"'c« = 0-099 Apt = 0-036 



P2/P0C 



U.56 



RAKE 
NO. 


TUBE NO, 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0,931 


O.9I+I+ 


0.958 


0.965 


0.951 


0,937 2 


0.935 


0.91+1 


0.950 


0.965 


O.96I+ 


0,961 


3 


0.91+6 


0.951 


0.961 


O.96I+ 


0.91+9 


0,950 1+ 


0.9^5 


0.91+1+ 


0.951 


0.953 


0.91+9 


0.9^5 


5 


0.91+8 


O.9I+9 


0.956 


0.91+1+ 


0,9^9 


0.939 6 


0.950 


0,951+ 


0.961 


0.963 


0.960 


0.959 



M^= 1.75 



a 



0.0° 



nio^oo = 0.521 



P,7p,^= 0.925 1^1 /m^- 0>Q8T Ap^^ = 



0.070 



Exit setting 



Po/P. 



i^.32 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.887 


0.899 


0.915 


0.931 


0.93^ 


0.929 


2 


0.889 


0.900 


0.925 


0.91+3 


0.9^7 


0.91+0 


3 


0.901 


0.908 


0.927 


0.936 


0.933 


0,929 


1+ 


0.920 


0.926 


0.933 


0.927 


0.918 


0,901+ 


5 


0.926 


0.93^ 


0.952 


0.927 


0.927 


0.911 


6 


0.903 


0,921+ 


0.91+1+ 


0.951 


0,91+9 


0,937 



Moo = 



1.75 



a = 



0.0° 



iDo/nioo = 0.521 Exit setting =_ 



Ptg/Pt = 0-8^^ m^i/moo = 0.078 Ap^_^ = 0-081+ 



Pg/Poo ^ 



1+.02 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 
0.857 


2 


3 


1+ 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.870 


0,889 


0,901+ 


0,910 


0,891 


2 


0.859 


0.870 


0.889 


0.901+ 


0.915 


0,909 


3 


0.857 


0.865 


0,871+ 


0.881 


0,885 


0.878 


1+ 


0.859 


0.873 


0.88U 


0.893 


0,902 


0,895 


5 


0.855 


0,873 


0,901 


O.91I+ 


0.930 


0.927 


6 


0.856 


0.871 


0.885 


0.891 


0,888 


0,876 



32 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, Ptp/Pt ■ Continued 
(a) 1.50 D inlet vith vortex generators 



Moo = 1.7? 



a = 



0.0^ 



^nMoo = 



0.^21 



Pt^/Pt Z_M^ iPhi/rnco= Q>Q9g Apt. 



0.050 



Exit setting = B 



RAKE 
NO. 

1 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


h 


5 


6 


0.936 


Q.okk 


0.961 


0.981 


0.957 


0.9ii.l 


2 


0.9i^3 


0.9113 


0.952 


0.968 


0.980 


0.98I1 


3 


0.9*^6 


0.951 


0.963 


0.976 


0.963 


0.979 


h 0.939 


0.939 


0.956 


0.972 


0.982 


0.979 


5 


o.9i^o 


0.9^5 


O.96T 


0.965 


0.951 


0.958 


6 0.91^2 


0.953 


0.973 


0.977 


0.981 


0.982 



Mco= 1>T5 



a = 



0.0° 



mo/moo = 0,521 



Exit setting = B 



Ptp/Pt = 0-932 mhi/rBoo= 0.080 a 



Pts 



0.068 



P^/Pcc = ^-32 



RAKE 
NO. 


TUBE NO. 


RAKE. TUBE NO. | 


1 


2 


3 


h 


5 


6 


NO. 

1 


2 


3 


k 


5 


6 


1 


0.895 


0.911 


0.931 


o.9k6 


0.932 


0.92I+ 


2 0.898 


0.912 


0.933 


0.914.8 


0.957 


0.956 


3 


0.906 


0.916 


0.939 


0.952 


0.9^3 


0.9^+7 


k 0.9114. 


0.925 


0.939 


0.914.1 


0.925 


0.919 


5 


0.923 


O.9UO 


0.956 


0.929 


0.926 


0.913 


6 0.917 


0.9^+3 


0.958 


0.951+ 


0.9^5 


0.93^ 



Moo 



1.75 



Pt^/Pt^ =_^ 



a = 0.0° 

n^n/i.^= 0.068 



/m^ = 0.521 



"0/"'oo 



^Ptp = 



Exit setting 



0.081 



P2/P00 



3.9^ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0,860 


0.875 


0.893 


0.906 


0.905 


0.893 


2 


0.872 


0.879 


0.890 


0,908 


0.917 


0.915 


3 


0.852 


0.862 


0.870 


0.881 


0.893 


0.886 


k 


0.865 


0.873 


0.883 


0.899 


0.908 


0.908 


5 


0.862 


0.879 


0.895 


0.897 


0.925 


O.92I+ 


6 


0.858 


0.866 


0.877 


0.887 


0.898 


0.901 



M = 



1.75 



a = 



0.0° 



Pt /Pt = Q'960 mbi/moo= 0.079 ^Pt2 



mo/^oo = 



0.521 



0.066 



Exit setting = 2 



U.5U 



RAKE 
NO. 

1 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 
0.921 


2 
0.91^2 


3 


1^ 


5 


6 


1 


2 


3 


1+ 


5 


1 6 
0.985 


0.967 


0.9814. 


0.957 


0.91+2 


2 


0.930 


0.936 


0.960 


0.975 


O.98I+ 


3 


0.935 


0.950 


0.969 


0.982 


0.963 


0.979 


1+ 


0.922 


0.929 


0.958 


0.978 


O.98I1 


0.983 


5 


0.929 


0.91+5 


0.970 


0.966 


0.953 


0.963 


6 


0.935 


0.955 


0.978 


0.978 


0.983 


0.982 



33 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^^Pt " Continued 
(a) 1.50 D inlet with vortex generators 



Moo= 1-T5 



a = 



0.0° 



/in^= 0^521 



"0/ *"oo 



Pt^/Pt ° °-93T mblAoc- °-°^Q Apt, 



0.059 



Exit setting = 



RAKE 


TUBE NO. 


RAKE TUBE NO. 


NO. 


1 


2 


3 


h 


5 


6 


NO. ^ 


2 


3 


k 


5 


6 


1 


O.90I+ 


O.92U 


0.9^5 


0.955 


0.936 


0.923 


2 0.908 


0.922 


0.9^2 


0.957 


0.959 


0.95I+ 


3 


0.910 


0.926 


0.9U1 


0.956 


0.938 


0.9i^-i^ 


h 0.920 


0.929 


o.9i+i 


0.9U1 


0.93^+ 


0.925 


5 


0.926 


0.9^3 


0.957 


0.93^ 


0.93^ 


0.923 


6 0.925 


0.9^^3 


0.958 


0.956 


0.95^ 


0.9i+2 



K.--H^ 



a = 



0.0 



^t2/Pt«, = Q-Q98 mtji/nioo = Q' 



060 



mo/nio 



^Pt, 



0.521 



Exit setting =_ 



0.080 



P^/Po) 



RAKE 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.863 


0.881 


0.902 


0.922 


0.919 


0.905 


2 


0.87^ 


0.882 


0.901 


0.920 


0.930 


0.93^ 


3 


0.862 


0.880 


0.888 


0.892 


0.899 


0.895 


k 


0.863 


0.880 


0.893 


0.908 


0.920 


0.926 


5 


0.869 


0.888 


0.909 


0.901 


0.918 


O.91J+ 


6 


0.866 


0.88^ 


0.898 


0.911 


0.922 


0.907 



"»= 1-^^ 



a = 



0.0' 



mo/m, 



/n.<„= 0.1^66 



Exit setting 



P,7p^. = 0.969 m,,i/in^= 0-107 Ap^^ = 



0.050 



Ps/Pco 



3.59 



RAKE 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


k 


5 


6 


1 0.983 


0.978 


0.965 


0.963 


0.959 


0.9i^9 


2 


0.991 


0.980 


0.975 


0.961 


0.963 


0.96ij- 


3 


0.986 


0.977 


0.963 


0.963 


0.961 


0.965 


i^ 


0.985 


0.978 


0.971 


0.962 


0.965 


0.966 


5 


O.98J+ 


0.978 


0.966 


0.9ij-2 


0.955 


0.959 


6 


0.982 


0.970 


0.963 


0.962 


0.965 


0.965 



1.55 



P,A =^^ 



a = 



n>biA 



0.0° mo/moo = 0.^66 

= 0.093 Ap =: 0.0i^8 



^t2 



Exit setting =____A_ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


k 


5 


6 
0.978 


1 


0.91+1 


0.9^5 


0.967 


0.981 


0.967 


0.953 


2 


0.939 


0.9^5 


0.956 


0.976 


0.979 


3 


0.951 


0.960 


0.979 


0.985 


0.97^ 


0.983 


1+ 


0.914-0 


0.914-6 


0.973 


0.985 


0.985 


0.983 


5 |o.9itl 


0.959 


0.977 


0.962 


0.963 


O.97U 


6 


o.9i)-9 


0.962 


0.983 


0.983 


0.983 


0.983 



3^ 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, VtJ^t " Continued 
(a) 1.50 D inlet with vortex generators 



Moo 



Pt: 



1.55 



a = 



0,0' 



"o/^oo = . 



0.1^66 



Jvt =_2:^E— i^biAoo = 0-0^9 Ap^^ = 0-076 



Exit setting = ^ 

P^/Poo - g'99 



RAKE 
NO. 


TUBE NO. J 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


k 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.837 


0.8l^7 


0.856 


0.869 


0.880 


0.868 


2 


0.850 


0.857 


0.873 


0.888 


O.89I+ 


0.881+ 


3 


0.8JH 


0.852 


0.87!^ 


0.883 


0.891 


0.893 


1| 


0.837 


0.81+8 


0.861 


0.869 


0.877 


0,881 


5 


0.85i^ 


0.872 


0.885 


0.87*<^ 


0.893 


0.895 6 


0.81+9 


0.865 


0,882 


0.895 


0.903 


0.903 



Hx, = J^55. 



a = 



0.0' 



Pt^/Pt = Q'9T9 mHi/iPoo= Q'096 



23o/inoo 

^Pt2 



0.466 



Exit setting =_ 



O.OU8 



vjv^ - 3.62 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.987 


0.988 


O.98I+ 


0.971+ 


0.963 


0.951 


2 


0.986 


0.985 


0.996 


0.982 


0.973 


0.971 


3 


0.991 


0.993 


0.990 


0.979 


0.967 


0.969 


1+ 


0.985 


O.98I+ 


O.99I+ 


0.978 


O.97I+ 


0.971 


5 


0.990 


0.990 


0.988 


0.952 


0.961 


0.963 


6 


0.998 


0.993 


0.980 


0.973 


0.970 


0.970 



^= 1-^^ 



a = 



0.0' 



WiDoo = 0-^66 



Pt^/Pt =^l96l_ mH,/m^= Q-08T Ap^^ 



0.038 



Exit setting 



B 



3.50 



RAKE 
NO. 


TUBE 


NO. 




RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.966 


0.968 


0.959 


0.961 


0.956 


0.937 


2 


0.97*^ 


0.971 


0.966 


0.959 


0.959 


0.961 


3 


0.968 


0.962 


0.959 


0.960 


0.957 


0.961 


1+ 


0.972 


0.968 


0.962 


0.960 


0.961 


0.963 


5 [0.968 


0.967 


0.959 


0.938 


0.950 


0.953 


6 


0.961 


0.957 


0.959 


0.959 


0.962 


0,963 



Moo 



1.55 



a = 



0.0° 



^t>t = "-Q^ -bi/in„=^£55. 



-2' "^00 



nio/iDoo = 



0.1+66 



0.073 



Exit setting 
P2/P00 



B 



3.05 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 
0.880 


3 


h 


5 


6 


1 


0.861 


0.872 


0.883 


0.900 


0.899 


0.888 


2 


0.872 


0.889 


0.902 


0.912 


0.909 


3 


0.859 


0.868 


0.883 


0.903 


0.903 


0.907 h 


0.851 


0.861 


0.877 


0.892 


0.903 


0.905 


5 |o.8t4 


0.887 


0.897 


0.890 


0.911 


0.91^ 6 


0.863 


0.876 


0.890 


0.90^^- 


0.916 


0.911 



35 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, Vt Jvf 
(a) 1.50 D inlet with vortex generators 



Continued 



a = 



0.0' 



^n/^o 



0.1^66 






c 



Exit setting = 

P2/P0C » 3-'^2 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 

2 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.98!^ 


0.988 


0.986 


0.97^ 


0.962 


O.9I+8 


0.982 


0.982 


0.995 


0.9^3 


0.963 


0.971 


3 


0.989 


0.992 


0.988 


0.979 


0.967 


0.968 


1+ 


0.981 


0.980 


0.99I+ 


0.978 


0.973 


0.970 


5 


0.988 


0.988 


0.988 


0.9^^3 


0.95^^ 


0.958 


6 


0.997 


0.993 


0.982 


0.971 


0.970 


0.969 



Mco 



1.55 



a 



0.0' 



Ptp/Pt = 0-963 ^W^oo= 0-063 



mo/nioo = 



^Ptp = 



0.466 



Exit setting 



0.060 



Pa/Poc = 3A3 



RAKE 
NO. 


TUBE NO. 1 RAKE 


TUBE NO. I 


1 


2 


3 


h 


5 


6 ^^"• 


1 


2 


3 


4 


5 


6 


1 


0.927 


0,9^^ 


0.964 


0.984 


0.959 


0.948 2 


0.938 


0.943 


0.962 


0.978 


\ — ■ 

0.981 


0.980 


3 


0.9^7 


0.958 


0.965 


0.981 


0.965 


0.971 4 


0.934 


0.944 


0.966 


0.980 


0.984 


0.983 


5 


0.938 


0.948 


0.969 


0.963 


0.957 


0.968 6 


0.945 


0.958 


0.983 


0.984 


0.984 


0.983 



Moc = 



1.55 



a = 



0.0° 



WPt = 0-901 mm /moo = 0-0^0 



nio/moo 

^Pt2 



0.ii66 



Exit setting 



0.075 



P2/P00 



3.10 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.872 


0.884 


0.898 


0.909 


0.915 


0.903 


2 


0.882 


0.891 


0.906 


0.920 


0.926 


0.928 


3 


0.867 


0.879 


0.891 


0.901 


0.912 


0.918 


4 


0.861 


0.879 


0.897 


0.903 


0.915 


0.920 


5 


0.877 


0.898 


0.915 


0.903 


0.923 


0.923 


6 


0.874 


0.885 


0.896 


0.910 


0.927 


0.921 



a = 



2.0° 



Mco= 3-00 
PtA = °-^98 m,i/m^= 0-1^3 



mo/lDoo = 



Exit setting =_ 



0.098 



P^/Pco ^ 



31.52 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.860 


0.879 


0.885 


0.892 


0.906 


0.898 


2 


0.881 


0.897 


0.891 


0.907 


0.916 


0.948 


3 


0.899 


0.890 


0.900 


0.919 


0.939 


0.896 


4 


0.860 


0.873 


0.879 


0.896 


0.904 


0.892 


5 


0.874 


0.875 


0.873 


0.892 


0.895 


0.897 


6 


0.898 


0.904 


0.933 


0.927 


0.946 


0.916 



36 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p^ - Continued 
(a) 1.50 D inlet with vortex generators 



Moo 



3.00 



a = 



2.0° 



m_/n 



Ptg/Pt = 0-Q93 iPhlAcc- 0-109 



Ap 



t2 



O.IOU 



Exit setting = B 

P^/Poc ' 31-31 



RAKE 
NO. 


TUBE NO. 1 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


h 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.862 


0.879 


0.882 


0.889 


0.899 


0.889 


2 


0.875 


0.893 


0.889 


o.90i+ 


0.906 


0-9^3 


3 


0.901 


o.88i^ 


0.898 


0.917 


0.928 


0.893 


k 


0.851 


0.863 


0.866 


0.887 


0.896 


0.883 


5 


0.875 


0.870 


0.873 


0.888 


0.885 


0.880 


6 


0.897 


O.90U 


0.931 


0.926 


0.937 


0.9-13 



Moo 



3.00 



a 



2.0° 



Ptp/Pt = Q'887 ii>^nAoo = Q'Q99 



nio/moo 

^Pt2 



Exit setting 



0.098 



P^/Pco = 31.08 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1^ 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.862 


0.877 


0.881 


0.887 


0.890 


0.883 


2 


0.874 


0.897 


0.892 


0.900 


0.900 


0.93*+ 


3 


0.897 


0.875 


0.891 


0.908 


0.917 


0.883 h 


O.Qk-J 


0.858 


0.860 


0.880 


O.88J1 


0.869 


5 


0.869 


0.86i^ 


0.866 


0.879 


0.872 


0.866 6 


0.892 


0.898 


0.930 


O.92U 


0.931 


0.908 



Moc= 2-T5 



a = 



2.0'^ 



./i 



'0/"^oo 



Exit setting 



Pt.7Pt. = 0.911 ^^/m^= 0-121 Ap^, 



0.092 



P2/P00 



21.^7 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.909 


0.891 


0.912 


0.899 


0.926 


0.876 


2 


0.893 


0.905 


0.888 


0.921 


0.936 


0.933 


3 


0.921 


0.917 


0.938 


0.939 


0.91^5 


0.921 


k 


0.871 


0.881 


0.871 


0.895 


0.926 


0.955 


5 


0.910 


0.887 


0.891 


0.918 


O.S2k 


0.911 


6 


0.911 


0.913 


0.922 


0.923 


0.92i+ 


0.881 



M 



2.75 



a = 2.0' 



nio/nioo = 



V^/v^ = 0-910 i^-L/m^= 0.112 



An 



't2 



0.097 



Exit setting = B 



RAKE 

NO. 


TUBE NO. J 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.907 


0.887 


0.908 


0.895 


0.923 


0.886 


2 


0.890 


0.903 


0.890 


0.919 


0.923 


0.911 


3 


0.925 


0.903 


0.939 


0.926 


0.91+14- 


0.911+ 


k 


0.870 


0.882 


0.876 


0.902 


0.926 


0.958 


5 


0.922 


0.890 


0.899 


0.913 


0.926 


0.911 


6 


0.921 


O.91I+ 


0.934 


0.927 


0.930 


0.874 



37 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p^ - Continued 
(a) 1.50 D inlet with vortex generators 



Mco= 2-75 



a = 



2.0' 



Pt^/Ptoo = Q'903 m^i/m^ = Q'Q97 



"0/^00 = 



^Ptp = 



Exit setting = 



0.112 



vj\ 



21.07 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.899 


0.880 


0.900 


0.889 


0.920 


0.881 


2 


0.875 


0.899 


0.891 


0.910 


0.906 


0.888 


3 


0.918 


O.89U 


0.927 


0.913 


0.930 


0.913 


\ 


0.858 


0.873 


O.86I1 


0.891 


0.911 


0.960 


5 


0.910 


0.87^ 


0.883 


0.902 


0.915 


0.901 


6 


0.921 


0.915 


0.9^0 


0.936 


4.935 


0.879 



Moo = 2.50 



a 



2.0' 



m, 



o/™oo = 



Exit setting = 



Pt^/Pt^, = 


0.930 m^i/irioo = 


0.13^ ^Ptp = 


0.06^ 


? 




P,/p^ = lU.88 


RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


ll 


5 


6 


1 


2 


3 


\ 


5 


6 


1 


0.917 


0.903 


0.928 


0.917 


0.91^1 


0.922 


2 


0.905 


0.919 


0.910 


0.9^2 


0.950 


0.953 


3 


0.939 


0.939 


0.9U0 


0.936 


0.9i^U 


0.912 


h 


0.897 


0.910 


0.926 


0.91^2 


o.9^U 


0.958 


5 


0.9^^-1 


0.916 


0.931 


0.931 


0.933 


0.916 


6 


0.926 


0.927 


0.9^6 


0.953 


0.95^^ 


0.929 



Mcx) = 2.50 



a 



2.0* 



™oA 



Exit setting = B_ 



^'t2/Pt^ = 0.924 i"bl/^oo = 0.112 ^Pt2 = 



0.100 



vjv^ - 1^.63 



RAKE 


TUBE NO. 


RAKE 
NO, 


TUBE NO. 


NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.915 


0.898 


0.924 


0.912 


0.933 


0.914 


2 


0.902 


0.916 


0.909 


0.947 


0,940 


0.948 


3 


0.930 


0.936 


0.956 


0.935 


0.940 


0.900 


4 


0.866 


0.883 


0.911 


0.938 


0.949 


0.958 


5 


0.927 


0.902 


0.927 


0.919 


0.920 


0.903 


6 


0.929 


0.930 


0.947 


0.946 


0.948 


0.922 



Hx) = 2.50 



a = 2.0' 



mji 



nirv. = 



Exit setting = 



Pts/Ptoo = Q'920 m^i/nioo = 0.094 



^Pt, 



0,120 



P^P^ = 14.48 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.910 


0.892 


0.922 


0.909 


0.927 


0.908 


2 


0.901 


0.918 


0.918 


0.945 


0.928 


0.942 


3 


0.917 


0.924 


0.951 


0.948 


0.949 


0.895 


4 


0.846 


0.862 


0.898 


0.935 


0.955 


0.957 


5 


0.916 


0.890 


0.914 


0.^19 


0.912 


0.894 


6 


0.930 


0.932 


0.946 


0.947 


0.948 


0.916 



38 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p. - Continued 
(a) 1.50 D inlet with vortex generators 



Mco = g>2^ 



a = 



2.0' 



oA 



m^/m, 



Pt2/Ptoo = 0.9^1 ^bl/"^oo = O.llj-7 ^Pt^ 



0,078 



Exit setting = A 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.930 


0.930 


0.91+ii 


0.952 


0.946 


0.939 


2 


0.930 


0.933 


0.951 


0.955 


0.955 


0.962 


3 


0.902 


0.918 


0.929 


0.937 


0.91+3 


0.91+0 


1+ 


0.895 


0.910 


0.933 


O.9I+8 


0.961 


0.968 


5 


0.927 


0.928 


0.91+2 


O.9IJ-I1 


0.952 


0.950 


6 


0.938 


0.91+2 


0.954 


0.958 


0.961 


0.961 



Moo = 2.2^ 



a 



2.0* 



ifio/^^oo = 



Exit setting = B 



Pt^/Pt^ = 


0.936 m^i/moo = 


0.108 Ap^^ = 


0.097 






P./p„ = 9.95 


RAKE 
NO. 


TUBE NO. 


RAKE 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


NO. 


1 


2 


3 


4 


5 


6 


1 


0.927 


0.921 


0.943 


0.950 


0.934 


0.925 


2 0.920 


0.926 


0.949 


0.954 


0.947 


0.963 


3 


0.885 


O.90I+ 


0.928 


0.91+5 


0.952 


0.953 


4 0.877 


0.896 


0.922 


0.940 


0.957 


0.967 


5 


0.915 


0.917 


0.936 


O.9I+2 


0.947 


0.945 


6 0.937 


0.942 


0.954 


0.958 


0.960 


0.960 



Meo= 2.25 



a = 2.0' 



m, 



)/""oo = 



Ptp/Pt 



0.919 



"bl/^oo 



0.094 -^Ptp = 



0.128 



Exit setting = C^ 

P2/P00 = _ 



9.77 



RAKE 




TUBE NO, 


RAKE 
NO. 


TUBE NO. 


NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 1 0.906 


0.909 


0.933 


0.954 


0.930 


0.922 


2 


0.888 


0.904 


0.936 


0.953 


0.922 


0.944 


3 


0.851 


0.868 


0.895 


0.924 


0.946 


0.956 


4 0.843 


0.861 


0.888 


0.909 


0.932 


0.953 


5 


0.870 


0.882 


0.911 


0.936 


0.936 


0.955 


6 0.918 


0.925 


0.953 


0.958 


0.961 


0.957 



Moo = 2.00 



a = 



2.0' 



Pt2/Pto, = 0-921 m^i/mcc = 0.117 



^o/"^oo = 
_ ^Pt2 = 



0.089 



Exit setting = 

Pp/p = 
2^ 00 



6.63 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.904 


0.921 


0.947 


0.945 


0.938 


0.924 


2 10.888 


0.893 


0.918 


0.957 


0.927 


0.950 


3 


0.887 


0.896 


0.899 


0.897 


0.893 


0.881 


4 


0.880 


0.889 


0.912 


0.928 


0.935 


0,926 


5 


0.899 


0.918 


0.933 


0.921 


0.935 


0.925 


6 


0,921 


0.933 


0.961 


0.962 


0.953 


0.950 



39 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p. /p. - Continued 
(a) 1.50 D inlet with vortex generators 



M^ = 2.00 



a 



2.0° 



^oh 



nir^/m^ = 



Ptp/Ptoo = Q'92Q ^blA 



0.083 Apt2 = 



Exit setting = 



Pg/Po 



6.10 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.912 


0.926 


0.91^7 


0.9^5 


0.929 


0.910 


2 


0.895 


0.903 


0.927 


0.956 


0.935 


0.9i)-6 


3 


0.880 


0.891 


0.896 


0.900 


0.902 


0.896 


h 


0.875 


0.883 


0.907 


0.906 


0.922 


0.918 


5 


0.907 


0.915 


0.937 


0.929 


0.93^ 


0.925 


6 


0.935 


O.9U7 


0.955 


O.9I19 


0.948 


0.950 



Moo = 



2.00 



a = 



2.0' 



^oh 



m^/in^ = 



Exit setting = 



Pt^/Pt^ - 0-928 m^i/m^ = 0.079 Ap^^ = 



0.100 



Pp/p^ = 6.^9 
^ 00 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.919 


0.917 


0.9^5 


0.95'+ 


0.935 


0.925 


2 


0.920 


O.92U 


0.950 


0.949 


0.942 


0.954 


3 


0.873 


0.888 


O.90U 


0.922 


0.931 


0.936 


4 


0.871 


0.884 


0.899 


0.915 


0.929 


0.940 


5 


0.907 


O.92I+ 


O.9I12 


0.93^ 


0.942 


0.932 


6 


0.933 


0.944 


0.955 


0.958 


0.962 


0.963 



Moo = _i:Tl 



a 



2.0' 



^0/^00 



Exit setting = A 



Pt>t^= 0-9^5 inti/in^= 0.112 Ap^ 



0.066 



vjv^ = ^-^^ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.91^2 


0.946 


0.952 


0.967 


0.957 


0.945 


2 


0.942 


0.950 


0.966 


0.967 


0.956 


0.951 


3 


0.931 


0.94U 


0.949 


0.948 


0.938 


0.924 


4 


0.929 


0.932 


0.932 


0.927 


0.917 


0.905 


5 


0.91^8 


0.947 


0.955 


0.93^ 


0.941 


0.922 


6 


0.947 


0.952 


0.963 


0.968 


0.962 


0.958 



Moo = 1-75 



a = 2.0' 



Pts/Pt^ = Q-944 ra^i/m^ = O.08U 



mo/moo 

^Pt2 



Exit setting = B 



0.070 



p7p = ^.57 
2^ 00 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.932 


0.942 


0.958 


0.977 


0.949 


0.926 


2 


0.938 


0.939 


0.965 


0.967 


0.957 


0.956 


3 


0.914 


0.925 


0.935 


0.941 


0.940 


0.941 


4 


0.910 


0.919 


0.936 


0.941 


0.938 


0.935 


5 0.948 


0.943 


0.956 


0.936 


0.939 


0.925 


6 


0.941 


0.949 


0.970 


0.974 


0.970 


0.963 



i+0 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p.^ /p^ - Continued 
(a) 1.50 D inlet with vortex generators 



Moo = 1*15 



a = 



2.0° 



^oAco = 



Pts/Ptoo = Q'930 ™bi/^oo = 0.083 Ap^^ = 0.106 



Exit setting 



pA 



ij-.50 



RAKE 
NO. 


TUBE NO. 


RAKE 


TUBE NO. 


1 


2 


3 


k 


5 


6 


NO. 


1 


2 


3 


k 


5 


6 


1 


0.958 


0.970 


0.970 


0.935 


0.905 


0.875 


2 


0.966 


0.96^ 


0.91^-6 


0.918 


0.912 


0.912 


3 


0.9^5 


0.933 


0.920 


0.920 


0.900 


0.913 


k 


0.938 


0.933 


0.929 


0.921^- 


0.92i^ 


0.921^ 


5 


0.951 


0.9^8 


0.925 


0.902 


0.905 


0.908 


6 


0.973 


0.958 


0.925 


0.912 


0.911 


0.913 



Moo = 1-55 



a 



2,0' 



"o/n'oo = 



Exit setting = 



Pts/Ptoo = 0.966 mbi/mpo = 0.120 Ap^^ = 0.0^1^ 



P^/Pco = 



3-57 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.991 


0.988 


0.978 


0.96h 


0.952 


o.9te 


2 


O.99U 


0.975 


0.965 


0.959 


0.961 


0.962 


3 


0.96JJ- 


0.965 


0.961 


0.964 


0.963 


0.965 


k 


0.959 


0.960 


0.962 


0.965 


0.968 


0.968 


5 


0.966 


0.970 


0.965 


0.9i^2 


0.959 


0.951 


6 


0.983 


0.978 


0.962 


0.960 


0.962 


0.963 



M^= 1.55 



a = 2.0* 



Pt^/Pt^ = 0.965 ^blA 



0.088 



^Pt2 = 



0.061 



Exit setting 



P2/P. 



3.53 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


1 

TUBE NO. 1 


1 


2 


3 


h 


5 


* 6 


1 


2 


3 


k 


5 


6 


1 


0,989 


0.988 


0.981 


0.966 


0.950 


0.932 


2 


0.991 


0.976 


0.964 


0.960 


0.962 


0.963 


3 


0.966 


O.96U 


0.961 


o.96i+ 


0.963 


0.965 


h 


0.960 


0.960 


0.963 


0.965 


0.967 


0.967 


5 


0.967 


0.972 


0.96i+ 


0.943 


0.956 


0.951 


6 


0.988 


0.979 


0,962 


0.961 


0.962 


0,963 



Moo = 1.55 



a = 2.0* 



oA 



m^/m 



Exit setting = 



Pts/Pt^ = 0-965 niblA 



0.077 ^H, 



0.065 



P^/Pc^ = 3.51 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0,987 


0.988 


0.984 


0.967 


0.949 


0.930 


2 


0.993 


0.979 


0.964 


0.961 


0.963 


0.936 


3 


0.967 


0,964 


0.962 


0.965 


0.964 


0.966 


4 


0,958 


0.960 


0.964 


0.967 


0.968 


0.968 


5 


0.969 


0.973 


0.963 


0.943 


0.955 


0.951 


6 


0.989 


0.982 


0.963 


0.963 


0.963 


0.964 



Ui 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p^ - Continued 
(a) 1.50 D inlet with vortex generators 



M^ = 3>00 



a = 5.0' 



^oh 



m^/ni^ = 



Exit setting 



A 



Ptp/Ptco ^ Q-T99 ^bi/^00 = 0-098 Ap^^ 



0.208 



Pp/Poo = 



28.30 



RAKE 
NO. 


TUBE NO. 


RAKE 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


NO. 


1 


2 


3 


1+ 


5 


6 


1 


0.781 


0.806 


0.829 


0.81+2 


0.857 


0.81+6 


2 


0.780 


0.808 


0.81+7 


0.863 


0.887 


0.836 


3 


0.803 


0.805 


0.793 


0.771 


0.71+8 


0.735 


1+ 


0.778 


0.766 


0.7^3 


0.735 


O.72I+ 


0.721 


5 


O.80I+ 


0.791 


0.775 


0.763 


0.7^5 


0.733 


6 


0.800 


0.835 


0.868 


0.862 


0.861 


0.822 



l^^ = 3-00 



a = 



5.0' 



"o/i 



m^/m^ = 



Exit setting 



Ptp/Ptoo = 0.800 m^i/m^ = 0.087 Ap^^ = O.207 



pA 



28.0if 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.780 


O.80U 


0.830 


0.81+2 


0.855 


0.8if3 


2 


0.753 


0.780 


0.816 


0.853 


0.887 


o.Skk 


3 


0.721 


0.729 


0.75^ 


0.777 


0.800 


0.80ii 


k 


0.72^ 


O.7U1 


0.765 


0.791 


0.806 


0.797 


5 0.738 


0.762 


0.778 


0.802 


0.812 


0.786 


6 


0.770 


0.81^ 


0.866 


0.870 


0.857 


0.846 



Moo= 3-00 



a 



5.0' 



njn 



Exit setting 



Ptj/Pt = 0-793 m^i/moo = 0.091 Ap^^ = 0.256 



Ps/Pa 



27.87 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


h 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.799 


0.817 


0.836 


0.844 


0.852 


0.841 


2 


0.740 


0.768 


0.813 


0.852 


0.875 


0.907 


3 


0.708 


0.712 


0.737 


0.770 


0.813 


0.836 


4 


0.704 


0.712 


0.726 


0.755 


0.787 


0.809 


5 


o.70i+ 


0.712 


0.73^^ 


0.761 


0.800 


0.828 


6 


0.743 


0.780 


0.832 


0.882 


0.899 


0.851 



Moo = 2.75 



a = 5.0' 



Pts/Pt = 0.813 n^bl/^oo = 0.111 



hIq/it 



^Pt, 



Exit setting = A 



0.157 



P^/Pco = 19-23 



RAKE 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.826 


0.81+2 


0.851+ 


0.836 


0.832 


0.812 


2 


0.788 


0.810 


0.836 


0.855 


0.876 


0.875 


3 


O.75I+ 


0.767 


0.781 


0.802 


O.82I+ 


0.821 


1+ 


O.7I+8 


0.759 


0.768 


0.788 


0.810 


0.801 


5 


0.756 


0.768 


0.786 


0.803 


0,821+ 


0.819 


6 


0.798 


0.815 


0.837 


0.85I+ 


0,861+ 


0.863 



1+2 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY LATA, p^ /p^ - Continued 
(a) 1.50 D inlet vith vortex generators 



M^= g-7^ 



a = 



5.0° 



^o/™oo = 



Exit setting = 



B 



Pts/Ptoo = 0-809 °ibi/^oo = 0.101 Ap^2 = 0.199 



P^P^ = i9>oo 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.823 


0.81^1+ 


0.862 


0.838 


0.826 


0.806 


2 


0.777 


0.800 


0.829 


0.850 


0.881 


0.887 


3 


0.736 


0.753 


0.778 


0.803 


0.830 


0.836 


k 


0.727 


0.737 


0.756 


0.781 


0.811 


0.811 


5 


0.736 


0.7ij-7 


0.771 


0.79^ 


0.820 


0.831 


6 


0.786 


0.809 


0.836 


0.861 


0.878 


0.870 



Moo= 2.75 



a = 5.0° 



m, 



o/™c» = 



Exit setting = C 



Pt2/Ptoo = 0.802 m^i/m^ = 0.089 Ap^^ = 0.232 



P^/Pc^ = 



18.78 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


k 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.816 


0.81+1 


0.865 


0.81+2 


0.820 


0.796 


2 


0.771 


0.792 


0.823 


0.853 


0.885 


0.896 


3 


0.721 


0.73^ 


0.759 


0.790 


0.826 


0.841 


k 


0.709 


0.721 


0.7I+I 


0.765 


0.802 


0.809 


5 


0.720 


0.732 


0.75^ 


0.782 


0.81U 


0.835 


6 


0.775 


0.800 


0.832 


0.862 


0.883 


0.869 



M^= 2-50 



a = 



5.0' 



Pts/Pt^ = 0.825 "'bl/^oo = 0.121 



1'o/"'oo = 
^Pt2 = 



Exit setting 



0.172 



P^/Pco = 13-37 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


1 

TUBE NO. 1 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.833 


0.852 


0.867 


0.885 


0.890 


0.887 


2 


0.813 


O.82I+ 


0.81+0 


0.856 


0.878 


0.876 


3 


0.766 


0.773 


0.781+ 


0.797 


0.811 


0.813 


k 


0.760 


0.768 


0.779 


0.792 


0.807 


0.800 


5 


0.767 


0.775 


0.789 


0.802 


0.823 


O.82I+ 


6 


0.812 


0.825 


0.852 


0.883 


0.897 


0.902 



Hx,= 2.50 



a = 5.0° 



Pt2/Pt<„ = 0.828 ni^i/nioo = 0.107 



nio/°'oo 

^Pt2 



0.190 



Exit setting = 

P2/Poc = 



13.28 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.839 


0.857 


0.868 


0.889 


0.879 


0.875 


2 0.816 


0.827 


0.81+5 


0.868 


0.89I+ 


0.898 


3 


0.760 


0.767 


O.78I+ 


0.80I+ 


0.826 


0.838 


1+ 


O.7I+8 


0.756 


0.771 


0.786 


0.808 


0.808 


5 


0.759 


0.768 


O.78I+ 


0.805 


0.830 


0.81+5 


6 


0.810 


O.82I+ 


0.861 


0.896 


0.903 


0.905 



h3 



TAELE II.- ENGINE-EACE PRESSURE RECOVERY DATA, Pt^/Ptoo " Continued 
(a) 1.50 D inlet vith vortex generators 



Mco= 2-^Q 



a = 



5.0° 



Ptp/Pt 



0.823 



,iA 



0.093 



^o/^oo 
^Pt2 



Exit setting = 



0.210 



P^/Poo = 



13.12 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1^ 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.836 


0.853 


0.868 


0.889 


0.87i^ 


0.867 


2 


o.8oi+ 


0.815 


0.841 


0.866 


0.892 


0.905 


3 


0.7*4-2 


0.750 


0.77^ 


0.80»^ 


0.832 


0.8i^8 


1^ 


0.732 


0.7^5 


0.761 


0.783 


0.801 


0.801; 


5 


0.7^3 


0.753 


0.77^ 


0.799 


0.821^ 


0.8i+5 


6 


O.80I+ 


0.821 


0.863 


0.901 


0.901 


0.895 



M<„= 2.25 



5.0' 



Pt^/Ptoo = 0-Q^T m^i/m^ = O-lSi^ 



mo/lDoo = 
_^Pt2 = 



0.159 



Exit setting = 



P2/P0 



9.38 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.896 


0.899 


0.903 


0.916 


0.896 


0.886 


2 


0.885 


. 881 


0.890 


0.898 


0.907 


0.905 


3 


0.821 


0.823 


0.823 


0.827 


0.836 


0.830 


h 


0.815 


0.822 


0.821 


0.833 


O.8I13 


0.832 


5 


0.835 


0.833 


0.836 


0.825 


0.857 


O.85I; 


6 


0.883 


0.881 


0.908 


0.9^3 


0.928 


0.953 



M^= 2-2^ 



5.0' 



n'o/'^oo = 



p^ /p^ = 0.863 mbi/nioo = 0^100^ Ap^, 



0.185 



Exit setting = 

P2/Pco = 



9.23 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.893 


0.893 


0.908 


0.916 


0.882 


0.863 


2 


0.876 


0.878 


0.890 


O.90U 


0.919 


0.912 


3 


0.805 


0.806 


O.SU 


0.827 


0.81^3 


0.81^8 


h 


0.789 


0.802 


0.808 


0.821 


0.833 


0.829 


5 


0.821 


0.82i^ 


0.832 


0.823 


0.858 


0.865 


6 


0.878 


0.878 


0.916 


0.91+8 


0.922 


0.932 



Moo = 2.25 



a = 



5.0^ 



Ptp/Pt = 0.856 in^l/™oo = 0.083 



_ ^Pt2 = 



0.207 



Exit setting = C 

. Pp/p 



= 9.08 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.889 


0.890 


0.902 


0.912 


0.877 


0.852 


2 


0.869 


0.87U 


0.886 


0.901 


0.918 


0.909 


3 


0.788 


0.797 


0.809 


0.828 


0.8J^8 


0.859 


k 


0.768 


0.786 


0.788 


0.802 


0.820 


0.825 


5 


0.810 


0.805 


0.812 


0.811 


0.858 


0.870 


6 


0.872 


0.878 


0.913 


0.9U5 


o.9ii<- 


0.931 



kh 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p.^. - Continued 
(a) 1.50 D inlet with vortex generators 



Mco = 



2.00 



a 



5.0° 



mju 



Exit setting = 



Ptp/Ptoo = 0.8^9 ™b 1/^00 = 0.102 Ap^ = 0.189 



pA 



6.12 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.882 


0.912 


0.939 


0.932 


0.901 


0.859 


2 0.852 


0.863 


0.879 


0.911 


0.915 


o.90ii- 


3 


0.812 


0.818 


0.811 


O.80I; 


0.796 


0.785 


k O.Qlh 


0.825 


0.830 


0.833 


0.822 


0.797 


5 


0.8^^-2 


O.8UO 


0.828 


0.790 


0.797 


0.780 


6 0.886 


0.916 


0.938 


0.933 


0.932 


0.9U2 



Mco 



2.00 



a = 



5.0° 



"o/'^oo = 



Exit setting = B 



Pt^/Pt 



0. 



"b 1/^00 = 0.080 Ap^^ = 0.162 



P^/Po 



= 6.13 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.901 


0.926 


0.9U0 


0.928 


0.899 


0.857 


2 


0.881 


0.901 


0.907 


0.907 


0.906 


0.893 


3 


0.823 


0.823 


0.820 


0.820 


0.822 


0.809 


h 


0.803 


0.800 


0.799 


0.800 


0.820 


0.802 


5 


0.8^7 


o.8i^8 


0.857 


0.838 


0.860 


0.848 


6 


0.904 


0.923 


0.937 


0.940 


0.939 


0.926 



M^ = 2.00 



a = 



5.0^ 



^tj^t^ = 0.871 ™bl/™oo = 0.071 



JDo/^oo = _ 




_ Exit setting = 




^Pt2 = 


0.169 


Pp/P^ = 



= e.ih 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.901 


0.920 


0.934 


0.936 


0.905 


0.866 


2 


0.887 


0.911 


0.918 


0.916 


0.909 


0.900 


3 


0.829 


0.825 


0.824 


0.827 


0.836 


0.829 


4 


0.795 


0.800 


0.804 


0.810 


0.808 


0.805 


5 


0.851 


0.848 


0.848 


0.832 


0.862 


0.858 


6 


0.907 


0.928 


0.942 


0.939 


0.929 


0.927 



Ko = 1.75 



a = 5.0' 



Ptp/Pt^ = 0.926 111^1/^00= 0.119 



^Ptp = 



0.082 



Exit setting = 

vJv 

£1 { 



= k.3h 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.966 


0.968 


0.970 


0.943 


0.914 


0.894 


2 


0,922 


0.906 


0.906 


0.914 


0.915 


0.906 


3 


0.920 


0.939 


0.952 


0.952 


0.943 


0.926 


4 


0.896 


0.897 


0.900 


0.904 


0.910 


0.910 


5 


0.920 


0.937 


0.950 


0.933 


0.944 


0.940 


6 


0.904 


0.902 


0.912 


0.934 


0.944 


0.926 



J+5 



TABLE II.- ENGINE-FACE PRESSURE RECOATERY DATA, p^ /p^ - Continued 
(a) 1.50 D inlet vith vortex generators 



Moo 



1.75 



a 



5.0^ 



"o/^ 



mr^/m^ = 



Exit setting = 



Ptp/Pt 



0.921 ini3i/moo = 0>086 Ap^2 = 0.112 



P^Pco = ^'^3 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


h 


5 


6 


1 


O.96I+ 


0.969 


0.96i+ 


0.927 


0.896 


0.866 


2 


0.924 


o.90i+ 


0.908 


0.925 


0.917 


0.902 


3 


0.917 


0.933 


0.939 


O.9I1O 


0.9i+2 


0.933 


k 


0.879 


0.883 


0.886 


0.889 


0.895 


0.895 


5 


0.917 


0.935 


0.9^3 


0.92k 


0.9^3 


0.939 


6 


O.9OI1 


0.902 


0.911+ 


0.931 


0.9i+7 


0.91+9 



Moo = _ii75 



a 



^.0° 



fio/^oo = 



Exit setting = 



Ptp/Ptoo ^ 0.918 "^blAoo = 



0.07^ ^Ptp = 



0.12^ 



P^/Pco = ^-28 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.963 


0.969 


0.961 


0.920 


0.887 


0.85^ 


2 


0.92^ 


0.90!^- 


0.907 


0.929 


0.920 


0.899 


3 


o.9ii+ 


0.930 


0.932 


0.93^ 


0.935 


0.928 


k 


0.872 


0.876 


0.879 


0.88U 


0.89^ 


0.887 


5 


0.91^1 


0.930 


0.936 


0.919 


0.91^0 


0.936 


6 


0.905 


0.902 


0.91^1 


0.929 


0.95^ 


0.96i^- 



M<„ = 1.55 



a 



5.0° 



"oA 



Exit setting = 



Ptj/Pt = 0-950 m^i/moo = 0-109 Ap^, 



0.081 



p^p^ = 3-1+6 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1^ 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.989 


0.988 


0.981 


0.957 


0.939 


0.916 


2 


O.9I+6 


0.91+6 


0.951+ 


0.957 


O.9I+2 


0.951 


3 


0.936 


0.951 


0.958 


0.961 


0.962 


0.961 


1+ 


0.912 


0.918 


0.922 


0.926 


0.932 


0.932 


5 


0.936 


0.957 


0.969 


0.951+ 


0.968 


0.967 


6 


0.945 


O.9I+I+ 


0.955 


0.957 


0.959 


0.959 



Moo = 1-55 



a 



5.0° 



n^o^oo = 



Exit setting = B 



Pt2/Pt = o>9^9 ^bi/^oo = 0-079 ^Ptp = Q-086 



vJv = 3.^2 

2" 00 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


O.98I+ 


0.990 


0.981+ 


0.962 


0.931+ 


0.909 


2 


0.951 


O.9I+6 


0.951 


0.951+ 


0.91+9 


0.950 


3 


0.934 


0.950 


0.960 


0.963 


0.965 


0.963 


1+ 


0.908 


0,909 


O.91I+ 


0.917 


O.92I+ 


O.92I+ 


5 


0.931 


0.952 


0.969 


0.957 


0.968 


0.970 


6 


O.9I+8 


0.91+5 


0.953 


0.955 


0.958 


0.959 



1+6 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p^ - Continued 
(a) 1.50 D inlet with vortex generators 



He = 1-55 



a = 5-0' 



"oAoo = 



Exit setting = C 



Pta/Ptoo = 0-9^7 m^i/moo = 0-069 Ap^ = 0.096 



P^/Pco = 3.38 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


h 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.983 


0.987 


0.982 


0.957 


0.935 


0.905 


2 


0.950 


0.9^5 


0.951 


0.95^ 


0.949 


0.950 


3 


0.933 


0.952 


0.959 


0.963 


0.966 


0.960 


1^ 


0.896 


0.905 


0.909 


0.912 


0.918 


0.9114- 


5 


0.930 


0.9^9 


0.965 


0.955 


0.965 


0.969 6 


0.9l^7 


0.9^5 


0.95^ 


0.956 


0.957 


0.958 



hi 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, Vtjv^ " Continued 
(b) 1.50 D inlet without vortex generators 



Moo = 3.00 



a = 0.0*- 



mo/raoo = 0-999 



Exit setting 



Ptg/Ptoo = 0.907 ™bl/™oo = 0.1^7 '^Pts - 0.1^^ 



P2/P0 



U-29 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.862 


O.89I+ 


0.9i+6 


0.952 


0.896 


0.857 


2 


0.868 


0.921 


0.952 


0.971 


0.906 


0.855 


3 


0.86U 


0.905 


0.955 


0.972 


0.899 


0,&^h 


k 


0.867 


0.908 


0.951 


0.963 


0.912 


0.864 


5 


0.866 


0.899 


0.92? 


0.969 


0.909 


0.859 


6 


0.863 


0.915 


0.962 


0.95^ 


0.883 


0.850 



M«, = 3.00 



a = 0.0<^ 



mjm^ = 0.999 



Exit setting = A 



Pt2/Pt<„ = 0.882 n'bl/"'oo = 0.111 ^Vt^ = 0.1.6k 



Pa/Pc 



= 29.9'^ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.820 


0.872 


0.9^+^ 


o.9te 


0.876 


0.825 


2 


0.830 


0.895 


0.9^+0 


0.928 


0.900 


0.821 


3 


0.821 


0.873 


0.936 


0.936 


0.901 


0.827 


h 


0.831 


0.896 


0.959 


0.937 


0.868 


0.820 


5 


0.827 


0.879 


0.939 


0.9»^3 


0.859 


0.8lit 


6 


0.824 


0.887 


0.959 


0.952 


0.867 


0.819 



M„ = 3.00 



a = 0.0° nio/ni<„ = 0.999 

Pts/Pt^ = 0.777 "bl/^'co = 0.087 ^Pt2 = 0.332 



Exit setting 



P2/P00 = 25-79 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.663 


0.666 


0.715 


0.835 


0.893 


U.7YY 


2 


0.668 


0.705 


0.808 


0.921 


0.897 


0.755 


3 


0.666 


0.691 


0.781 


0.903 


0.899 


0.773 


U 


0.666 


0.687 


0.764 


0.891 


0.868 


0.771 


5 


0.665 


0.683 


0.762 


0.909 


0.906 


0.777 


6 


0.663 


0.674 


0.735 


0.855 


0.897 


0.782 



Moo = 3.00 



a = 0.0"= 



mo/moo = 0.99 



Exit setting 



Pts/Ptoo '^ 0.890 rabl/"oo = 0.100 ^Pt2 = 0.166 



Ps/Po = 30.19 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.846 


0.908 


0.956 


0.918 


0.855 


0.825 


2 


0.842 


0.906 


0.949 


0.960 


0.894 


0.832 


3 


0.840 


0.898 


0.95'+ 


0.957 


0.879 


0.830 


4 


0.834 


0.880 


0.938 


0.959 


0.895 


0.838 


5 


0.840 


0.887 


0.943 


0.962 


0.886 


0.8,37 


6 


0.869 


0.950 


0.958 


0.884 


0.827 


0.8l4 



48 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, Pt Vp^ - Continued 

(b) 1.50 D inlet without vortex generators 



Moo = 3>00 



a = 0.0*^ 



no/^co = Q'999 



Exit setting = _C_ 



Ptp/Ptoo = 0>86^ i"bl/^oo = 0.080 Ap^2 - 0.19^ 



P^/Pco = 28-82 



RAKE 
NO. 


TUBE NO. 


RAKE 
HO. 


TUBE NO. 


1 


2 


3 


1^ 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.827 


0.9li^ 


0.950 


0.878 


0.799 


0.783 


2 


0.821 


0.901 


0.9ij-i+ 


0.9^1 


O.8I12 


0.795 


3 


O.83I+ 


0.91^ 


0.9^5 


0.853 


0.789 


0.783 


k 


0.817 


0.888 


0.9^+7 


0.930 


O.8U0 


0.79^ 


5 


0.808 


0.881 


0.931 


0.9^+5 


O.Qhs 


0.797 


6 


0.809 


0.89^ 


0.9^+2 


0.933 


O.83U 


0.791 



Moo = ^.00 



oc = O^QQ 



ino/^00 = 0,999 



Exit setting = C 



Pts/Ptoo = 


0.797 


nibl/'"oo = 


0.069 


^Pt2 = 


0.315 






P^/Poo = 25 


•53 


RAKE 
NO. 


TUBE NO. 


RAKE 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


NO. 


1 


2 


3 


h 


5 


6 


1 


0.761 


0.890 


0.903 


0.785 


0.70*^ 


0.691 


2 


0.733 


0.869 


0.938 


0.855 


0.737 


0.702 


3 


0.805 


0.926 


0.882 


0.761 


0.697 


0.691 


h 


0.7^9 


0.866 


0.917 


0.801 


0.709 


0.692 


5 


0.722 


0.82i+ 


0.9^+1 


0.88i+ 


0.739 


0.703 


6 


0.779 


0.926 


0.920 


0.797 


o.70iv 


0.693 



M^= 2.75 



a = 0.0° 



mo/m„ = 0.938 



Exit setting = A^ 



Pt2/Pt = 0.918 i"bl/"^oo = 0,139 ^Pt2 "" Q-10^ 



P^/Peo = gl>T7 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 






TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.886 


0.9^0 


0.928 


0.935 


0.953 


0.897 


2 


0.902 


0.9^+6 


0.922 


0.912 


0.9iti+ 


o.dSk 


3 


0.893 


0.951 


0.929 


0.918 


0.9^+3 


0.873 


k 


0.888 


0.935 


0.951 


0.938 


0.951 


0.889 


5 


0.891 


0.9^1 


0.937 


0.915 


0.93^^ 


0.867 


6 


0.882 


0.939 


0.950 


0.917 


0.926 


0.857 



Mco = 2.75 



a = 0.0° 



mo/moo = 0.938 



Exit setting = A 



Pts/Ptoo = 0.887 ni^lAoo = 0.102 ^Pt2 = 0.201^ 



P2/P0C = 20-50 



RAKE 
NO. 


TUBE NO. 


RAKE 


TUBE NO. 1 


1 


2 


3 


1+ 


5 


6 


NO. 


1 


2 


3 


k 


5 


6 


1 


0.791 


0.824 


0.908 


0.958 


0.966 


0.895 


2 


0.789 


0.831 


0.910 


0.956 


0.961 


o.mh 


3 


0.791 


0.8lif 


0.898 


0.95^ 


0.962 


0.907 


h 


0.790 


0.803 


0.885 


0.958 


0.970 


0.883 


5 


0.792 


0.827 


0.916 


0.957 


0.963 


0.900 


6 


0.789 


0.817 


0.891 


0.95^^ 


0.960 


0.886 



k9 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /pt - Continued 
(b) 1.50 D inlet without vortex generators 



Moo = 2.7^ 



a = O.QO 



"0/^00 = 0.938 Exit setting = A 



Ptp/Pt 



).8l6 ^bl/"^oo = 0>08U Ap^2 = 0,33^ 



P^/Poc = ^8,39 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.688 


0.706 


0.792 


0.903 


0.955 


O.82U 


2 


0.688 


0.711 


0.790 


0.916 


0.9^0 


0.821 


3 


0.690 


0.718 


0.820 


0.935 


0.9^5 


0.830 


k 


0.688 


0.708 


0.787 


0.891 


0.961 


0.819 


5 


0.690 


0.713 


0.823 


0.937 


0.9^3 


0.829 


6 


0.690 


0.71? 


0.825 


0.932 


0*9^2 


0.811 



Moo = 2.75 



a = 0.00 



^0/^00 = 0.938 



Exit setting = C 



Pta/Pt^ 



0.902 



"bl/^co 



0.102 



^Pt. 



0.162 



Ps/Pa 



20.75 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


k 


5 


6 


1 0.866 


0.95^ 


0.962 


0.93^ 


0.922 


0.852 


2 


0.816 


0.865 


0.950 


0.958 


0.910 


0.81+7 


3 0.823 


0.877 


0.9*^5 


0.961 


0.927 


0.853 


k 


0.8i+3 


0.910 


0.957 


0.961 


0.91+7 


0.862 


5 0.836 


0.903 


0.957 


0.959 


0.917 


0.830 


6 


0.830 


0.888 


O.9U9 


0.953 


o.?,35 


0.825 



^= 2.75 



a = 0.0° 



™o/"oo = 0.938 Exit setting = _C_ 



Pts/Pt = 0.853 m^l/moo = 0.085 ^Pt2 = O.2I+8 



P2/P00 = 19.07 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.779 


0.918 


0.937 


0.885 


0.886 


0.781+ 


2 


0.7^2 


0.769 


0.899 


0.9^ 


0.896 


0.797 


3 


0.753 


0.808 


0.915 


0.935 


0.888 


0.781+ 


k 


0.766 


O.85I+ 


0.937 


0.926 


0.901+ 


0.791 


5 


0.765 


0.859 


0.953 


0.922 


0.868 


0.763 


6 


0.753 


O.81I+ 


0.93^ 


0.936 


0.880 


0.763 



Moo = 2.50 



a = 0.00 



mo/nieo = 0.851 



Exit setting = A 



pt^/pt^ 



0.931 "'bl/'^oo = 



O.II+3 ^Pt2 " 0.103 



P^/P^ = II+.86 



RAKE 
NO. 


TUBE NO. 1 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.891 


0.928 


0.953 


0.960 


0.965 


0.922 


2 


0.886 


0.932 


0.950 


0.953 


0.959 


0.893 


3 


0.871 


O.92I+ 


0.9^+7 


0.953 


0.959 


0.913 


1+ 


0.891 


0.929 


0.951 


0.960 


0.967 


0.915 


5 


0.885 


0.927 


0.9I+8 


0.953 


0.957 


0.906 


6 


0.878 


0.930 


0.9^3 


0.952 


0.955 


0.897 



50 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p^ - Continued 

(b) 1.50 D inlet without vortex generators 



Moo = 2.'30 



a = 0.0*^ 



no/m^ = 0,851 



Exit setting = A_ 



Ptp/Ptoo = 0*91^ ^t)l/"^oo = 0,112 Ap^^ = 0,128 



Pp/Poo == ^^-19 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.859 


0.928 


0.962 


0.953 


0.957 


0.861 


2 


0.81^8 


0.923 


0.954 


0.941 


0.937 


0.859 


3 


0.846 


0.923 


0.955 


0.939 


0.937 


0.878 


k 


0.856 


0.922 


0.959 


0.954 


0.957 


0.867 


5 


0.850 


0.918 


0.9^+4 


0.9,3? 


0.91^7 


0.870 


6 


0.81t7 


0.917 


0.945 


0.939 


0.946 


0.857 



Moo = 2,^0 



a 



0,00 



mjm^ = 0,851 



Exit setting - A 



Pt^/Pt.^ = 


0.832 


•"b] 


7^00 = 


0.094 


-^Ptp = 0.308 






P2/Pc„= 12 


!-35 


RAKE 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.704 


0.787 


0.903 


0.923 


0.951 


0.796 


2 


0.695 


0.736 


0.827 


0.893 


0.930 


0.793 


3 


0.701 


0.752 


0.865 


0.913 


0.940 


0.804 


4 


0.702 


0.783 


0.896 


0.937 


0.938 


0.804 


5 


0.702 


0.753 


0.870 


0.918 


0.929 


0.804 


6 


0.703 


0.764 


0.884 


0.931 


0.937 


0.778 



M^= 2.50 



a = 0.0° 



iDo/m,^ = 0.851 



Ptg/Pt = 0.922 mbl/"oo = 0.103 Ap^2 = 0.109 



Exit setting = C 

vjv = 14.42 



RAKE 
NO. 






TUBE 


NO. 






RAKE 
NO. 






TUBE 


NO. 


1 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.865 


0.926 


0.959 


0.955 


0.957 


0.894 


2 


0.865 


0.931 


0.957 


0.956 


0.953 


0.859 


3 


0.862 


0.933 


0.957 


0.957 


0.956 


0.878 


4 


0.870 


0.927 


0.957 


0.956 


0.960 


0.881 


5 


0.865 


0.927 


0.954 


0.950 


0.954 


0.872 


6 


0.860 


0.927 


0.951 


0.946 


0.954 


0.862 



Moo = 2.50 



a = 0.0° 



nio/i"oo = Q>851 



Exit setting = C 



Pts/^t^ = 0.902 i^b 1/^00 = 0.086 ^Ptp = 0,l8U 



P^/Poo = 13>79 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.811 


0.889 


0.950 


0.961 


0.970 


0.844 


2 


0.804 


0.878 


0.938 


0.944 


0.967 


0.849 


3 


0.805 


0.876 


0.937 


0.943 


0.967 


0.873 


4 


0.816 


0.896 


0.953 


0.960 


0.967 


0.858 


5 


0.815 


0.896 


0.940 


0.953 


0.962 


0.852 


6 


0.809 


0.885 


0.941 


0.945 


0.965 


0.840 



51 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p. /p. - Continued 
(b) 1.50 D inlet withou" vortex generators 



Moo = 2^50 



a = 0.0° 



no/"ioo = 0-851 Exit setting = C 



Pt?-'Ptc 



0.859 m-^i/moo = 0.075 -^Ptp = 0.255 



P^/Poo = 12-81 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


)i 


5 


6 


1 


0.739 


0.835 


0.938 


0.951 


O.9I+O 


0.805 


2 


0.732 


0.803 


0.893 


0.936 


0.924 


0.799 


3 


0.7^^ 


0.836 


0.912 


0.9^+2 


0.933 


0.800 


k 


O.7UI+ 


O.8U7 


0.930 


0.951 


0.93^^ 


0.796 


5 


0.7^0 


0.833 


0.912 


0.9^ 


0.926 


0.793 


6 


0.737 


O.82U 


0.917 


0.9i^i^ 


0.937 


0.772 



Mco =2^25 



a = 0.0*^ 



no/m^o = -738 



Exit setting ~ A 



Pt^/Pt, 



0.9^9 



/moo = 0.132 Ap^^ = 0,062 



"bl/^'^00 



Pp/P^ = 9A 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.918 


O.9I+3 


0.959 


0.965 


0.969 


0.9'+8 


2 


0.912 


0.938 


0.955 


0.966 


0.967 


0.947 


3 


0.910 


O.9I+O 


0.955 


0.965 


0.965 


0.965 


)+ 


0.926 


0.9^+6 


0.951 


O.96U 


0.965 


0.950 


5 


0.925 


0.9^+3 


0.952 


0.9UU 


0.966 


0.9'+6 


6 


0.927 


0.947 


0.957 


0.962 


0.968 


0.937 



M^ = 2.25 



a = 0.0° 



no/n'c = 0-738 



Exit setting = _A_ 



Pt2/Pt^ = 0.937 ™tl/'"oo = 0.117 ^Pt2 = 0.087 



P?/Poo = 9.72 



RAKE 
NO. 


TUBE NO. 


RAKE 

NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.895 


0.92^ 


0.9^1^ 


0.960 


0.968 


0.9^0 


2 


0.887 


0.907 


0.935 


0.960 


0.967 


0,9^1 


3 


0.891 


0.902 


0.927 


0.956 


0.967 


0.961 


k 


0.89^ 


0.916 


0.9^1 


0.956 


0.969 


0.9^0 


5 


0.905 


0.933 


0.9^7 


o.9kk 


0.965 


0.9^1 


6 


0.902 


0.935 


0.951 


0.960 


0.962 


0.930 



Moo = 2.25 



a = 0.0^ 



^0/^00 = 0.738 



Exit setting = A 



Ptp/Pt^ = 0. 



%1 



Aoc = 0.081 ^Pt2 = 0.093 



Pp/Poo ^ 8.77 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.863 


0.903 


0.915 


0.904 


0.915 


0.885 


2 


0.845 


0.871 


0.905 


0.895 


0.899 


0.837 


3 


0.841 


0.861 


0.899 


0.892 


0.904 


0.858 


4 


0.866 


0.906 


0.916 


0.908 


0.914 


0.874 


5 


0.858 


0.887 


0.905 


0.897 


0.913 


0.844 


6 


0.846 


0.895 


0.910 


0.920 


0.917 


0.846 



52 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^. /p^ - Continued 

(b) 1.50 D inlet without vortex generators 



Moo = 2.2^ 



a 



0.0^ 



m^/m, 



A 



0,738 



Exit setting - C_ 



Pts/Ptoo " 0-9^0 ™bl/™oo = 0,092 



^Pt; 



0,090 



P^/Poo = 9^62_ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TOBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.89^i 


0.935 


0.957 


0.966 


0.966 


0.929 


2 


0.892 


0.93^ 


0-955 


0.967 


0.965 


0.92^ 


3 


0.88U 


0.927 


0.955 


0.965 


O.96U 


0.9^3 


k 


0,902 


o,9i^i 


0.951 


0.962 


0.965 


0.927 


5 


0,906 


0.9^0 


0,950 


0,9^5 


0.966 


0,91^1 


6 


0.909 


0.9^^ 


0.957 


0.962 


0.968 


0.913 



Moo - 2,25 



a = 0.0^ 



^oMo 



0.738 



Exit setting 



Pt^/Ptoo = 0,922 m^l/ 



m>,-i/Tn^ = 



0.07^ 



Apt2 = 0,109 



Pp/P^ = 9>25 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


• 


5 


6 


J 


2 


3 


h 


5 


6 


1 


0.868 


0.915 


0.91+3 


0.951+ 


0.963 


0.909 


2 


0.865 


0.901+ 


0.933 


O.9I+8 


0.956 


0.890 


3 


0.865 


0.896 


0.927 


O.9I+9 


0.957 


0.9li^ 


1| 


0.872 


0.912 


O.9U5 


0.955 


0.961 


0.905 


5 


0.873 


0.917 


0.9Uii 


0.938 


0.962 


0.901 


6 


0.870 


0.921 


O.9I+6 


0.955 


0.965 


0.898 



M„ = 2.25 


a = 0.0° 


mjm^= 0.738 


Exit setting = 


Ptg/Pt^ = 0.887 


™bl/™oo = 0.061 


Aptp = O.ll+l 


Pp/P^ 



8.59 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO, 


TUBE NO. 


1 


2 


3 


h 


s 


6 


1 


2 


3 


4 


5 


6 


1 


0.821 


0.900 


0.916 


0.922 


0.919 


0.879 


2 


0.808 


0.868 


0.916 


0.926 


0.909 


0.845 


3 


0.805 


0.854 


0.908 


0.919 


0.920 


0.852 


h 


0.833 


0.903 


0,920 


0,926 


0.915 


0.870 


5 


0.854 


0.898 


0.917 


0.894 


0.923 


0.829 


6 


0.840 


0,909 


0.927 


0.913 


0.930 


0.834 



M^ = 2.00 



a = 0.0*- 



iTio/moo = 0.625 



Exit setting = A 



Pt2/Ptoo " 0.958 ^bl/^oo = 0.123 ^Pt2 = 0.065 



Pp/P 
2 00 



6.81 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


)+ 


5 


6 


1 


0.926 


0.953 


0.960 


0.968 


0.979 


0.961 


2 


0.927 


0.953 


0.961 


0.963 


0.972 


O.96I+ 


3 


0.917 


O.9I+7 


0.959 


0.965 


0.975 


0.975 


k 


0.935 


0.952 


0.965 


0.971 


0.971+ 


0.951 


5 


0.935 


0.958 


0.967 


0.955 


0.976 


0.960 


6 


0.932 


0.956 


0.968 


0.972 


0.971+ 


0.962 



53 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p^ - Continued 
(b) 1.50 D inlet without vortex generators 



Moo 



2.00 



a = 0.0^ 



"oAoo = 0-^2^ 



Exit setting 



Pta/Ptcc = o.g^i^ "bi/™oo = 0.105 ^Pt2 = 0.091 



Ps/P. 



6.k9 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


1+ 


s 


6 


1 


0.892 


O.91I+ 


0.93^+ 


0.959 


0.957 


0.91+1+ 


2 


0.883 


0.896 


0.919 


O.9I+8 


0.968 


0.9^+8 


3 


0.887 


0.895 


0.913 


0.939 


0.965 


0.959 


1+ 


0.896 


0.912 
0.920 


0-935 
0.950 


0.960 
0.965 


O.96I+ 


0.9^2 


5 


0.891+ 


O.92I+ 


0.957 


0.951 


0.957 


0.952 


6 


0.900 


0.961 


0.9^8 



Moo = 2*00 



a 



0.0*^ 



n^/n 



0.625 



Exit setting 



Pta/Ptoo = _0i 



'blAoo = 0.085 Ap^^ = 0.121 



Po/P. 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.81+3 


0.863 


0.885 


0.906 


0.919 


0.901 


2 


0.81+0 
0.81+2 


0.85^ 


O.87I+ 


0.895 


0.910 


0.905 


3 


0.835 


0.8^6 


0.866 


0.881+ 


0.903 


0.911 


1+ 


0.853 


0.879 


0.902 


0.920 


0.907 


5 


0.850 


0.866 


0.888 


0.898 


0.928 


0.9^2 


6 


0.81+8 


0.864 


0.890 


0.91'+ 


0.929 


0.930 



Moo = 2-00 



a = 0.0° 



^nUo 



0,625 



Exit setting = C 



Pt2/Pt__ " 0>952 I"l3l/l"oo = 0,090 ^Pt2 = 0.082 



p7p^ - 6.59 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


s 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.912 


0.951 


0.962 


0.971 


0.975 


0.9^2 


2 


0.905 


0.945 


0.963 


0.968 


0.976 
0.972 


0.945 
0.931 


3 


0.899 


0.937 


0.960 


0.972 


0.976 


0.961 


1+ 


0.925 


0.952 


O.96I+ 


0.972 


5 


0.928 


0.960 


0.966 


0.955 


0.969 


0.929 


6 


0.932 


0.958 


0.968 


0.972 


0.975 


0.933 



Moo = 2.00 



a = 0.0*^ 



^o/"^oo 



= 0.625 



Exit setting = C 



Pt^/Pt^ " 0-93^ n^bl/^c« = 0.079 ^Ptp = 0.082 



p7p^ =6.3^ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.886 


0.920 


0.950 


0.957 


0.954 


0.925 


2 


0.886 


0.911 


0.935 


0.956 


0.955 


0.93^ 


3 


0.887 


0.900 


0.925 


0.949 


0.952 


0.941 


4 


0.902 


0.931 


0.952 


0.958 


0.951 


0.921 


5 


0.900 


0.947 


0.963 


0.939 


0.956 


0.929 


6 


0.896 


0.939 


0.963 


0.960 


0.958 


0.933 



5U 



TABLE II.- ENGINE-PACE PRESSURE RECOVERY DATA, p^ /p^ - Continued 
(b) 1.50 D inlet without vortex generators 



M^ = 2.00 



a 



0.0^ 



"oAoo = Q-6^^ 



Ptp/Pt 



0.900 



l^bl/'^^oo 



Q.067 ^Ptp = 0.123 



Exit setting 



P /p 



5.91 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


■ 
1 


2 


3 


1+ 


5 


6 


1 


0.853 


0.87^ 


0.895 


0.92^ 


0.9^^2 


0.917 


2 


0.848 


0.865 


0.890 


0.913 


0.930 


0.923 


3 


0.841^ 


0.859 


0.879 


0.905 


0.925 


0.9^+1 


h 


0.854 


0.865 


0.888 


0.919 


0.942 


0.916 


5 


0.863 


0.885 


0.903 


0.910 


0.955 


0.922 


6 


0.862 


0.881 


0.898 


0.932 


0.948 


0.918 



Moo = 1.75 



a = 0.0^ 



Pta/Ptoo = 0.953 



mQ/iDoo = 0.521 



Exit setting = A 



I'bl/"'co 



0.100 



^Pt= 



0.053 



P^/Po 



4.58 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 ■ 


5 


6 


1 


0.932 


0.955 


0.960 


0.965 


0.962 


0.954 


2 


0.918 


0.946 


0.963 


0.969 


0.962 


0.948 


3 


0.926 


0.948 


0.960 


0.967 


0.957 


0.954 


4 


0.939 


0.957 


0.955 


0.954 


0.953 


0.93^ 


5 


0.947 


0.963 


0.957 


0.946 


0.963 


0.944 


6 


0.944 


0.963 


0.963 


0.967 


0.966 


0.941 



Moo= 1.75 



a 



0.0^ 



^0/^00 = Qo^i 



Exit setting = A 



ptp/pt„ = 



0.937 



"bl/moo 



0.092 



^Ptp = 0.062 



P2/P00 = 



4.44 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.902 


0.915 


0.928 


0.946 


0.954 


0.938 


2 


0.903 


0.923 


0.941 


0,950 


0.950 


0.93^ 


3 


0.906 


0.922 


0.943 


0.956 


0.949 


0.932 


4 


0.929 


0.950 


0.949 


0.945 


0.935 


0.917 


5 


0.932 


0.958 


0.958 


0.933 


0.948 


0.925 


6 


0.921 


0.940 


0.959 


0.960 


0.953 


0.928 



M^ = 1.75 



a = 0.0^ 



m^/] 



Pt^/Pt^ = 0. 



%l/^^^oo 



m^ = 



0.078 



0/ ^00 
^Ptp 



0.521 Exit setting = _A. 
0.098 P^/Poo 



U.Ol 



RAKE 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.856 


0.866 


0.884 


0.899 


0.905 


0.885 


2 


0.856 


0.871 


0.891 


0.906 


0.924 


0.899 


3 


0.853 


0.862 


0.874 


0.880 


0.901 


0.882 


4 


0.859 


0.871 


0.885 


0.900 


0.912 


0.884 


5 0.857 


0.872 


0.894 


0.899 


0.940 


0.923 


6 


0.857 


0.870 


0.881 


0.891 


0.897 


0.897 



55 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, PtVpt - Continued 
(b) 1.50 D inlet without vortex generators 



Moo = 1.7^ 



a = 0.0^ 



°o/i°oo = 0-^21 



Exit setting = _C_ 



Pt-,/Ptoo = 0.9^7 "bl/^'oo = 0.077 '^Pts = 0-067 



Pj/Poo = '^'^1 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.929 


0.957 


0.958 


0.976 


0.975 


0.9^ 


2 


0.922 


0.960 


0.956 


0.969 


0.980 


0.959 


3 


0.916 


0.950 


0.958 


0.969 


0.976 


0.967 


h 


0.93^ 


0.960 


0.961 


0.971+ 


0.97^ 


0.9^1+ 


5 


0.931 


0.957 


0.966 


0.963 


0.973 


0.955 


6 


0.919 


0.952 


0.967 


0.980 


0.977 


0.91+5 



Mc« = 1-7^ 



a 



0.0"^ 



mJm^ 



= 0,521 



Exit setting 



Pts/Ptoo = 0>932 "^bl/^00 = 0,069 ^Ptp = Q'Q6T 



P^/Po. = A^30_ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.898 


0.918 


O.9I+O 


0.952 


0.953 


0.926 


2 


0.900 


0.917 


0.938 


0.953 


0.959 


0.919 


3 


0.899 


0.910 


0.92i+ 


0.939 


0.950 


0.936 


k 


0.913 


0.931 


O.9I+1+ 


0.935 


0.926 


0.908 


5 


0.921 


0.955 


0.961 


0.935 


0.91+0 


O.91I+ 


6 


0.919 


O.9U2 


0.960 


0.960 


O.9I+8 


0.916 



Moo = 1-75 



a = 0.0° 



oA 



^lr^/m, 



0,521 



Exit setting = C 



ptp/pt^ = 0. 



ratl/moo = 0.061 Ap^^ = 0.099 



P3/P00 = 3^ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.865 


0.880 


0.891 


0.911 


0.926 


0.897 


2 


0.875 


0.882 


0.892 


0.912 


0.932 


0.901 


3 


0.860 


0.868 


0.879 


O.89I+ 


0.903 


0.893 


k 


0.866 


0.878 


0.896 


0.912 


0.930 


0.896 


5 


0.869 


0.884 


0.902 


0.903 


0.91+9 


0.926 


6 


0.864 


0.873 


0.890 


0.909 


0.921 


0.892 



Moo = 1.55 



a = 0.0° 



mo/moo = 0.1+66 



Exit setting = A 



Ptp/Pt = 0.966 mbl/™oo = 0.106 APt2 = 0.0^2 



P^/Poc = 3^ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


]. 


2 


3 


h 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.980 


0.973 


0.957 


0.958 


0.961 


0.961 


2 


0.987 


0.982 


0.958 


0.956 


0.959 


0.958 


3 


0.982 


0.983 


0.960 


0.958 


0.961 


0.962 


k 


0.98i+ 


0.979 


0.960 


0.958 


0.962 


0.962 


5 


0.982 


0.976 


0.959 


0.9^1 


0.961 


0.962 


6 


0.991 


0.972 


0.958 


0.958 


0.961 


0.958 



56 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p^ - Continued 

(b) 1.50 D inlet without vortex generators 



Moo = 1.^^ 



a = 0.0'- 



™o/mco 



0.1^66 



Exit setting = ■A_ 



Pts/Ptoo = 0.969 "■bl/"'oo = 0.092 Apt = 0.061 



P2/P0C = 3^ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.926 


0.960 


0.978 


0.98i^ 


0.983 


0.97^ 


2 


0.932 


0.962 


0.982 


0.983 


0.98ii 


0.974 


3 


0.930 


0.962 


0.976 


0.983 


0.983 


0.981 


1^ 


0.932 


0.96k 


0.983 


0.98it 


0.984 


0.973 


5 


0.9,31 


O.96T 


0.980 


0.965 


0.981 


0.979 


6 


0.935 


0.970 


0.985 


0.983 


0.979 


0.972 



Moo = 1.55 



a = 0.0"- 



m„/m„ = 0.466 



Exit setting = A 



Pta/Ptoo = 0.869 



,iA 



0.059 Ap^^ = 0.088 



P2/P0 



= 2.81 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.832 


0.840 


0.853 


0.870 


0.889 


0.869 


2 


0.845 


0.854 


0.870 


0.885 


0.902 


0.868 


3 


0.839 


0.852 


0.866 


0.878 


0.896 


0.890 


4 


0.836 


0.841 


0.857 


0.871 


0.888 


0.870 


5 


0.848 


0.863 


0.874 


0.874 


0.907 


0.896 


6 


0.848 


0.862 


0.875 


0.890 


0.908 


0.876 



Moo = 1.55 



^tj^t = 0.974 



a = 0.0° 


mjm^ = 0.466 


Exit setting = 


mbl/raoo = 0.081 


Aptp = 0.049 


Pp/P™, 



= 3-53 



RAKE 
NO. 


1 1 

TUBE NO. 


1 — I 
RAKE 
NO. 


TUBE NO. j 


1 


2 


3 


4 


s 


6 


1 


2 


3 


4 


5 


6 


1 


0.97^ 


0.994 


0.971 


0.967 


0.967 


0.963 


2 


0.979 


0.997 


0.981 


0.967 


0.966 


0.962 


3 


0.973 


0.996 


0.982 


0.969 


0.967 


0.966 


4 


0.978 


0.996 


0.981 


0.968 


0.968 


0.964 


5 


0.980 


0.995 


0.973 


0.949 


0.966 


0.966 


6 


0.988 


0.993 


0.972 


0.966 


0.967 


0.961 



Moo = 1.^^ 



a - 0.0^ 



m^/m^ = 0.^66 



Ptp/Pt^ = 0,898 



"bl/^'^oo 



0.0^9 



^Pt: 



Exit setting = C 



0-075 



Pp/p 

2 o 



2.93 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.871 


0.887 


0.900 


0.914 


0.920 


0.890 


2 


0.883 


0.896 


0.901 


0.915 


0.930 


0.897 


3 


0.867 


0.875 


0.885 


0.899 


0.914 


0.900 


4 


0.869 


0.885 


0.893 


0.902 


0.919 


0.896 


5 


0.872 


0.890 


0.908 


0.903 


0.93^ 


0.918 


6 


0.874 


0.885 


0.896 


0.912 


0.926 


0.892 



57 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p^ - Continued 
(b) 1.50 D inlet without vortex generators 



M^ = 3-00 



a = 



"o/^ 



mr./m^ = 



Exit setting = 



Pto/Ptoo = 0-882 ni^i/^00 = 0,128 Ap^^ - 0,178 



P^/Poo = 30-61 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.809 


0.806 


0.829 


0.871+ 


0.93^ 


0.898 


2 


0.838 


0.882 


0.923 


0.949 


0.963 


0.862 


3 


O.Si+it 


0.888 


0.938 


0.950 


0.876 


0.834 


k 


0.872 


0.933 


0.889 


0.831 


0.814 


0.8l4 


5 


0.81+3 


0.88U 


0.932 


0.953 


0.903 


0.841 


6 


0.822 


0.851 


0.899 


0.945 


0.954 


0.859 



Moo = 3-00 



a = 2.0^ 



mJm^ = 



Exit setting = C 



Pt^/Ptoo == 0.873 "^bl/^oc = 0.101 Ap^^ = 0.187 



p7p^ - 30.18 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.798 


0.808 


0.859 


0.925 


0.947 


0.874 


2 


0.824 


0.868 


0.917 


0.951 


0.944 


0.847 


3 


0.825 


0.882 


0.946 


0.911 


0.828 


0.805 


4 


0.832 


0.922 


0.921 


0.873 


0.806 


0.795 


5 


0.812 


0.857 


0.938 


0.937 


0.860 


0.811 


6 


0.814 


0.843 


0.907 


0.958 


0.931 


0.841 



Mco = 2.75 



a 



2.0^ 



Pt2/H^ = 0.907 



n^oAoo = 



Exit setting = ^ 



)lA 



0.127 Ap^ = 0.142 



Pp/Poo = 21.30 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.869 


0.903 


0.932 


0.945 


0.946 


0.878 


2 


0.874 


0.928 


0.920 


0.931 


0.950 


0.854 


3 


0.852 


0.908 


0.916 


0.930 


0.957 


0.889 


4 


0.833 


0.869 


0.907 


0.933 


0.962 


0.879 


5 


0.851 


0.916 


0.913 


0.920 


0.956 


0.883 


6 


0.869 


0.918 


0.930 


0.935 


0.943 


0.855 



Moo = 2.75 



oc = 2.0^ 



^o/"^oo = 



Exit setting = C 



^tjv, = 



)i/" 



0.098 '^Pt2 " 0.197 



Ps/Pcc = 20.57 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.845 


0.896 


0.933 


0.942 


0.942 


0.861 


2 


0.799 


0.844 


0.919 


0.954 


0.93^ 


0.874 


3 


0.797 


0.820 


0.900 


0.915 


0.958 


0.914 


4 


0.793 


0.830 


0.907 


0.942 


0.969 


0.875 


5 


0.797 


0.826 


0.923 


0.910 


0.960 


0.896 


6 


0.807 


0.866 


0.930 


0.942 


0.943 


0.859 



58 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p^ - Continued 
(b) 1.50 D inlet without vortex generators 



Mco= 2«?0 



a 



= 2.0° 



'^o/^^ 



Exit setting = 



= A 



Ptg/Ptco = 0.927 "'bl/^oo = 0.138 Ap^^ = 0.078 



vJv = 1^^.83 



RAKE 
NO. 


TUBE NO. 


RAKE 


TUBE NO. 


1 


2 


3 


1; 


5 


6 


NO. 


• 
1 


2 


3 


h 


5 


6 


1 


0.903 


0.920 


0.925 


0.9^0 


0.9i+8 


0.909 


2 


0.895 


0.929 


0.935 


0.9i^8 


0.952 


0.901 


3 


0.888 


0.9^2 


0.952 


0.938 


0.9»^7 


0.899 


1+ 


0.903 


0.932 


0.9^9 


0.955 


0.961 


0.909 


5 


0.898 


0.938 


0.9^+6 


0.9^0 


0.950 


0.901 


6 


0.889 


0.918 


0.929 


0.9^7 


0.9*^8 


0.895 



Moo = 2.'^0 



a = 2.0° 



rajm^ 



Exit setting 



^tjvt^ = Q>918 ^bi/"^co = 0,099 -^Pt^ = 0*135 



vjv^ - ^h.k2 



RAKE 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.887 


O.92I+ 


0.929 


0.9^2 


O.9U9 


0.889 


2 


0.881 


0.932 


0.9^7 


O.9I+7 


0.953 


0.863 


3 

5 


0.853 


0.910 


0.958 


0.967 


0.9^+8 


0.886 


h 


0.81+3 


0.886 


0.933 


0.964 


0.960 


0.900 


0.858 


0.917 


0.960 


0.91+8 


0.9^+9 


0.881 


6 


0.870 


0.921 


0.937 


0.945 


0.952 


0.865 



M,, = 2,2^ 



a = 2.0'- 



nio/m^ = 



Exit setting 



Pt2/Pt^ " 0»9^Q ™blA 



0.129 ^Pt2 = O.IU7 



P^Pco = 9*87 



RAKE 
NO. 


1 1 

TUBE NO. 


1 1 

RAKE 
NO. 


1 1 

TUBE NO. 1 


1 


2 


3 


1+ 


■5 


6 


1 


2 


3 


4 


5 


6 


1 


0.923 


O.9I+6 


0.91+1 


0.953 


0.958 


0.930 


2 


0.918 


O.9I+I+ 


0.956 


0.951 


0.962 


0.945 


3 


0.903 


0.920 


0.933 


0.938 


0.91+1+ 


0.93^ 


1+ 


0.895 


0.913 


0.93^ 


0.952 


0.963 


0.946 


5 


0.913 


0.91+0 


0.956 


0.942 


0.966 


0.958 


6 


0.916 


0.945 


0.950 


0.955 


0.961 


0.930 



Moo = 2.2^ 



a = 2.0^ 



m^/rr 



Exit setting = C 



pt^/pt^ = 



0.920 ™bl/™oo = 0.093 '^Ptg = 0.093 



P2/P00 = 9.'t2 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.895 


0.928 


0.939 


0.958 


0.956 


0.915 


2 


0.882 


0.920 


0.946 


0.952 


0.955 


0.930 


3 


0.853 


0.871 


0.897 


0.925 


0.949 


0.953 


4 


0.847 


0.867 


0.894 


0.919 


0.944 


0.926 


5 


0.865 


0.888 


0.922 


0.943 


0.972 


0.932 


6 


0.902 


0.928 


0.943 


0.955 


0.958 


0.897 



59 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, Ptg/Pt^ " Continued 

(b) 1.50 D inlet without voi'tex .^^enera'.ors 



M^ = 2,00 



^0^ 



^o/^oo = 



Exit setting = A 



Pt:_VPtc 



0-917 



.lA 



0.100 ^Ptr " 0.096 



Pg/Pco = 6>^^ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 




5 


6 


1 


0.89^+ 


0.925 


0.950 


0.956 


0.9^^ 


0.928 


2 


0.876 


0.899 


0.920 


0.9^6 


O.961+ 


0.927 


3 


0.881 


0.891 


0.896 


0.898 


0.895 


0.879 


h 


0.877 


0.881+ 


0.902 


0.927 


0.932 


0.896 


5 


0.88U 


0.909 


0.933 


0.928 


0.9^7 


0.918 


6 


0.887 


0.925 


0.955 


0.963 


0.950 


0.918 



a = 2.00 



Meo = 2.00 



ir.Jn 



Exit setting = C 



0.083 Ap^^ = 0.096 



P^/Poo = A38_ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


.1 


2 


3 


1+ 


s 


6 


1 


0.903 


0.9^1 


0.9i+7 


0.955 


0.963 


0.927 


2 


0.903 


0.9^7 


0.950 


0.951 


0.957 


0.928 


3 


0.879 


0.892 


0.906 


0.925 


0.9^0 


0.935 


)t 


0.877 


0.889 


0.910 


0.929 


0.9'+2 


0.923 


5 


0.893 


0.923 


O.9I19 


0.93'^ 


0.966 


0.9^0 


6 


0.907 


0.9^7 


0.953 


0.961 


0.966 


0.922 



Moo = li75 



a = 2.0^ 



Ptp/:-t„ 



0.9^^3 



3l/n 



0.096 



/ 


Exit setting 


ra^/iTirv. - 


^Ptp = 0.070 


pA 



^.^0 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


s 


6 


1 


2 


3 


i+ 


S 


6 


1 


0.9ii0 


0.961 


0.953 


0.956 


0.970 


0.959 


2 


0.930 


0.963 


0.965 


0.963 


0.957 


0.936 


3 


0.919 


0.929 


0.9^5 


0.9^+6 


0.9^3 


0.925 


1+ 


0.926 


0.928 


0.923 


0.920 

1 


0.917 


O.90U 


5 


0.9U0 


0.960 


0.961 


0.938 


0.9^+7 


0.922 


6 


0.91+0 


0.958 


0.959 


O.96I+ 


0.963 


0.933 



Mc^ = 1.75 



2.0° 



mo^oo = 



Exit setting = C 



Ptp/Pt 



0.91+1+ 



)l/" 



0.071+ '^Ptp = 0.078 



vjv = i+.i+i 



RAKI-; 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.926 


O.9I+9 


O.96I+ 


0.976 


0.97^ 


0.91+1+ 


2 


O.92I+ 


0.958 


0.960 


0.961 


0.961 


0.953 


3 


0.913 


O.92I+ 


0.935 


O.9I+6 


0.9^9 


O.9I+1+ 


1+ 


0.903 


0.91^ 


0.925 


0.93^ 


0.91+3 


0.93*+ 


5 


,0.921+ 


0.952 


0.960 


0.939 


0.91+7 


0.922 


6 


0.927 


0.953 


0.968 


0.975 


0.966 


0.932 



60 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^. /p. - Continued 
(b) 1.50 D inlet without vortex generators 



Mco = 1*^^ 



2,0'' 



Pt^/Ptoo = 0- 



/^oo = 0.106 



"o/^ 



mn/m^ = 



Exit setting = A 



''hV'^'oo 



^Pt, 



= 0.056 



P /p 



3.55 



RME 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


; 1 


2 


3 


h 


5 


6 


1 


0.981 


0.996 


0.985 


0.972 


O.96I+ 


0.958 


2 


0.985 


0.993 


0.969 


0.959 


0.961 


0.958 


3 


0.970 


0.965 


0.960 


0.962 


0.963 


0.965 


h 


0.97^+ 


0.960 


0.962 


O.96I+ 


0.965 


0.965 


5 


0.987 


0.960 


0.958 


0.91+2 


0.962 


0.965 


6 


0.990 


0.983 


0.961 


0.960 


0.961 


0.958 



Moo = 1.55 



a = 2.0° 



oA 



m^/m, 



Exit setting = C 



Ptp/Pt^ = _q, 



5lA 



0.077 ^Pto = 0.051+ 



=/P^= 3.^5 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.975 


0.995 


0.978 


0.963 


0.962 


0.956 


2 


0.982 


0.990 


0.962 


0.957 


0.960 


0.957 


3 


0.964 


0.961 


0.958 


0.962 


0.963 


0.965 


k 


0.965 


0.959 


0.962 


O.96U 


0.965 


0.963 


5 


0.98U 


0.958 


0.958 


0.9^3 


0.963 


0.965 


6 


0.989 


0.980 


0.958 


0.959 


0.960 


0.955 



Moo = 3*00 



a = 5,0Q 



^nUoo = 



Exit setting = A 



Pt2/Pt„ 



0. 



)l/moo = 0.099 ^Pta = 0.222 



P2/P00 = 28.02 



1 1 

RAKE 
NO. 


1 

TUBE NO. 


I 1 

RAKE 
NO. 


1 

TUBE NO. 1 


1 


2 


3 


k 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.777 


0.812 


0.850 


0.881 


0.888 


0.809 


2 


0.759 


0.794 


0.834 


0.886 


0.893 


0.818 


3 


0.776 


0.808 


0.823 


0.795 


0.765 


0.739 


h 


0.768 


0.785 


0.789 


0.761 


0.736 


0.724 


5 


0.782 


0.825 


0.811 


0.785 


0.757 


0.735 


6 


0.762 


0.806 


0.859 


0.903 


0.896 


0.809 



3.00 



a 



5.00 



Pt^/Pt,, = a 



792 



51 A 



0.078 



. ^Pt2 



0.241 



Exit setting = C 
Pp/Pcc = 27.26 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.763 


0.810 


0.858 


0.884 


0.884 


0.789 


2 


0.736 


0.781 


0.837 


0.896 


0.889 


0.794 


3 


0.713 


0.721 


0.748 


0.771 


0.786 


0.765 


4 


0.713 


0.736 


0.768 


0.801 


0.804 


0.757 


5 


0.714 


0.731 


0.758 


0.789 


0.798 


0.772 


6 


0.73^ 


0.781 


0.844 


0.904 


0.895 


0.792 



61 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, Pt2/Ptoo " Continued 

(b) 1.50 D inlet without vortex generators 



Moo = 2.75 



a 



^.0^ 



p^ /p. = 0.810 m^i/moo = Q>Q9^ 



. ^Pt2 = 



0.201 



Exit setting - _A 

P^P. = 18.81 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.801 


0.835 


0.860 


0.873 


0.8it8 


0.790 


2 


0.775 


0.8li+ 


0.852 


0.868 


0.892 


0.8te 


3 


0.805 


O.82U 


0.802 


0.776 


0.756 


0.738 


k 


0.804 


0.817 


0.787 


0.763 


0.7'^5 


0.730 


5 


0.810 


0.825 


0.803 


0.775 


0.755 


0.738 


6 


0.775 


0.821 


0.855 


0.868 


0.889 


0.833 



Mcc = 2>75 



a = ^.0*^ 



njn 



Exit setting = C 



Pt/Pto 



0. 



n^l/m.^ = 0.087 Ap^^ = 0.267 



p./p. = 2M!L 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.82^+ 


0.859 


0.87i+ 


0.8li8 


0.839 


0.789 


2 


0.778 


0.809 


0.8i+2 


0.889 


0.917 


0.813 


3 


0.715 


0.731 


0.766 


0.808 


0.850 


0.822 


k 


0.701 


0.723 


0.752 


0.790 


0.821+ 


0.791 


5 


0.713 


0.727 


0.765 


0.808 


0.81+2 


0.817 


6 


0.769 


0.806 


0.851 


0.898 


0.908 


0.812 



M^= 2-50 



a 



5.0^ 



Pts^Pt = 0.815 in^l/i"oo = 0.091+ 



n>o/moo 

^Pt2 



0.221 



Exit setting 

Ps/Pa 



12.99 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.829 


O.85I+ 


0.860 


0.895 


0.898 


0.81+7 


2 


0.805 


0.836 


0.855 


0.871^ 


0.886 


O.83I+ 


3 


0.757 


0.757 


0.77*+ 


0.791 


0.793 


0.781 


1+ 


0.738 


0.7^8 


0.763 


0.776 


0.787 


0.773 


5 


0.753 


0.759 


0.775 


0.788 


0.800 


0.788 


6 


0.800 


O.82I+ 


0.852 


0.890 


0.919 


0.850 



M^ = 2>50 



a 



5.0'' 



mj: 



Itlfv. = 



p^^p^^ = 0,820 rn^iAoo = O.O83 ^Pts = 0*268 



Exit setting = _C 

p7p = 12.80 
id. 00 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


1+ 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.832 


0.866 


0.888 


0.888 


0.896 


0.836 


2 


0.799 


0.817 


0.81+4 


0.882 


0.915 


0.858 


3 


0.727 


0.7^0 


0.769 


0.799 


0.832 


0.828 


1+ 


0.716 


0.732 


0.760 


0.793 


0.806 


0.785 


5 


0.735 


0.752 


0.775 


0.803 


0.839 


0.830 


6 


0.792 


0.817 


0.859 


0.905 


0.935 


0.853 



62 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, p^ /p^ - Continued 
(b) 1.50 D inlet without vortex generators 



Moo = 2. 2^5 



a 



^>0Q 



°oAoo = 



Exit setting = _A_ 



Pts/Ptoo = 0>87^ ^lAico = 0,126 ^Pt2 = 



0-1^^ 



pA 



9.10 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.895 


0.912 


0.924 


0.920 


0.919 


0.888 


2 0.886 


0.896 


0.898 


0.906 


0.923 


0.905 


3 


0.827 


0.828 


0.83it 


0.837 


0.81+3 


0.838 


k 


0.817 


0.819 


0.830 


0.8^1 


0.81+5 


0.839 


5 


0.837 


0.81^1 


0.81+lf 


0.832 


0.857 


0.850 


6 


0.871 


0.901 


O.92U 


0.953 


0.950 


0.922 



Moo = 2.25 



a 



Pts/Ptoo = _qi86i+_ 



5.0^ 



lo/'Ooo = 



Exit setting = c 



nbl/™oo 



0.081+ 



Apt2 = 0.211 



P2/P^ = 8-73 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. \ 


1 


2 


3 


k 


5 


6 


1 


2 


3 


1+ 


5 


6 


1 


0.890 


O.90I+ 


0.901+ 


0.923 


0.909 


0.81+5 


2 


0.876 


0.886 


0.895 


0.917 


O.9I+2 


0.896 


3 


0.793 


0.803 


0.819 


0.837 


0.863 


0.858 


1+ 


0.776 


0.787 


0.799 


0.817 


0.830 


0.827 


5 


0.814 


O.81I+ 


0.826 


0.825 


0.871 


0.873 


6 


0.873 


0.896 


0.923 


0.959 


0.9I+I 


0.901 



M^ = 2,00 



a = 5.0^ 



Do/ir 



Pt^/Pt 



0.869 



/inoo = 



"bl/^"oo 



0,090 ^Pt2 = 0,177 



Exit setting = A 

Ps/Pco = ^ 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


T 


2 


3 


k 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.888 


0.933 


O.9I+8 


0.945 


0.922 


0.907 


2 


0.861 


0.877 


0.889 


0.921 


0.938 


0.877 


3 


O.82I+ 


0.825 


0.817 


0.812 


0.807 


0.795 


1+ 


0.825 


0.826 


0.838 


0.81+1+ 


0.836 


0.811 


5 1 0.852 


0.848 


0.836 


0.807 


0.808 


O.79I+ 


6 


0.897 


0.926 


0.939 


0.945 


0.946 


0.912 



M^ = 2,00 



a = 5.0O 



m. 



)/nioo = 



Exit setting = C 



Pts/Pt^o = 0>8^0 ni^i/nioo = 0.075 ^Ptp = 0.20^+ 



P^Pc.= 5.75 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 1 


1 


2 


3 


4 


5 


6 


1 


2 


3 


4 


5 


6 


1 


0.834 


0.859 


O.88I4 


0.898 


0.888 


0.860 


2 


0.850 


0.860 


0.824 


0.804 


0.797 


0.783 


3 


0.838 


0.856 


0.870 


0.882 


0.902 


O.912I 4 


0.822 


0.824 


0.820 


0.816 


0.820 


0.809 


5 


0.855 


0.877 


0.897 


0.890 


0.935 


O.903II 6 


0.849 


0.873 


0.833 


0.806 


0.799 


0.761 



63 



TABLE II.- ENGINE-FACE PRESSURE RECOVERY DATA, pt /pt - Concluded 
(b) 1.50 D inlet without vortex generators 



Moo= 1-75 



a 



5.0'' 



./ 



m^/m_ = 



Exit setting 



= A 



Ptp/Pt, 



0-931 



)lAoo = 0,103 ^Pt2 = 0.092 



Pp/Poo = ^-^7 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


k 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.957 


0.977 


0.975 


0.971 


0.9i^9 


0.918 


2 


0.9^3 


0.910 


0.899 


0.900 


0.900 


0.892 


3 


0.919 


0.933 


0.956 


0.969 


0.968 


0.959 


h 


0.911 


0.917 


0.917 


0.918 


0.915 


0.90^4^ 


5 


0.91*+ 


0.9^1 


0.963 


0.95^ 


0.972 


0.956 


6 


0.925 


0.902 


0.905 


0.906 


0.907 


0.898 



Moo= 1.75 



a = ^.0^ 



"oA 



Exit setting 



Ptg/Ptoo = 0.927 "'blAoo = 0.076 Ap^^ = 0.101 



P^/Poo = A3iL 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.951 


0.973 


0.975 


0.971 


0.951 


0.906 


2 


0.9^+2 


0.910 


0.900 


0.900 


0.900 


0.890 


3 


0.911 


0.9^+1 


0.960 


0.966 


0.968 


0.95^ 


k 


0.881 


0.889 


0.893 


0.897 


o.90i+ 


0.895 


5 


0.91^ 


0.9^5 


0.958 


0.9i+8 


0.971 


0.957 


6 


0.933 


0.902 


o.90i+ 


0.906 


0.907 


0.887 



Moo= 1-55 



a = ^.OQ 



mJm^ 



Exit setting = _A_ 



ptp/pt. 



).95i nibi/™oo = 0.096 Ap^2 = 0.08^ 



Pg/Pco = 3.^1 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


k 


5 


6 


1 


0.982 


0.99*+ 


0.982 


0.965 


0.951 


0.9it8 


2 


0.950 


O.9U2 


0.9^+7 


0.950 


0.951 


0.91+7 


3 


0.936 


0.953 


0.961 


0.963 


0.963 


0.95^ 


U 


0.913 


0.918 


0.923 


0.925 


0.930 


0.925 


5 


0.93^ 


0.9^9 


0,969 


0.957 


0.976 


0.970 


6 


O.9I+3 


0.9^5 


0.950 


0.952 


0.955 


0.951 



Moo = 1>55 



a = ^,0^ 



oA 



m^/m, 



Exit setting = C 



Ptp/Pt = 0,9^^8 mbi/^00 = 0,071 ^Pt2 = 0.098 



P^/Poo = 3>31 



RAKE 
NO. 


TUBE NO. 


RAKE 
NO. 


TUBE NO. 


1 


2 


3 


h 


5 


6 


1 


2 


3 


h 


5 


6 


1 


0.977 


0.99^+ 


0.979 


0.957 


0.951 


0.9^ 


2 


0.958 


0.9^3 


0.9^8 


0.951 


0.950 


0.9^+7 


3 


0.933 


0.953 


0.960 


0.962 


0.960 


0.9^8 


k 


0.901 


0.907 


0.908 


0.912 


0.917 


0.911 


5 


0.930 


0.952 


0.967 


0.956 


0.977 


0.96^^ 


6 


0.9^+9 


0.9^5 


0.951 


0.953 


0.955 


0.9^+8 



6k 






-1^ 

A ft 



8 t-' 



ON 



^ — ^ 




X K 



•H 

> 

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o 
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69 










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n 








n 1 


1.50 D inlet with 
vortex generators 
todified 1.75 D 




\ 


^s 


J 


inlet 
A Initial I.75 D 
inlet 




D 


V, 


-^ 


^ 




J 


k^ 






\ 


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% 


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'"bl 
nioo 



,12 



Figure 5«- Maximum performance, Mpg = 3*00, a = 0' 



,11^ 



71 



.92 



_pts 



.8k 



.76 











^ 


ED 










y 


^ 


/^ 










^ 


-^ 


/ 












/^ 


p^ 












/ 


r 














/ 


1> 






1.50 D inlet with 
vortex generators 
/Exit setting B \ 
Hx/R)iip = 2.330/ 

D 1.75 D modified 


















inlet 

/Exit setting a' \ 

Ux/R)iip = 2. 300;/ 



^Pt, 



.30 



.20 



.10 



^-^^^^ 



.06 



.08 



.10 
m^ 



.12 



.1^ 



Figure 6.- Supercritical performance; 1^ = 3«00^ a = 



72 






.92 



.88 



.8k 



.80 



.76 



.72 




<>A 



D 6 



O Bleed exit setting A 

□ Bleed exit setting B 

A Bleed exit setting C 

O Bleed exit setting D 



^Pt2 



,30 



on 



.10 







C 


t! 






















A 


h 




















<> 


































< 


"m 


as 


^V.A 
























^^ 


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4^ 


HX 


? 































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.06 



.08 



.10 



°>bl 



,12 



.14 



,16 



Figure 7-- Supercritical performance, I.50 D inlet with vortex generators; 

(x/R)iip = 2. 330; M^ = 3-00, a = 0°. 



73 



Pt 



Pt„ 



2_ .8k 




.30 



.20 



^Pt. 



,10 



% 
















\ 




V 


















\ 


















k 


^ 


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( 


!>— 




















%. 


^0-0 



























.06 



.08 



,10 



lHoo 



.12 



,li^ 



Figure 8. 



Effect of vortex generators, I.50 D inlet; bleed exit setting 
C, (x/R)iip = 2. 330; H» = 3.00, a = 0°. 



7k 



en 

o 



en 



o 
o 



o 




o 





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d H 



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p 



















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.06 



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mbl 



Figure 1^.- Inlet unstart angles of attack for various degrees of 
supercritical operation, I.50 D inlet with vortex generators; 
(x/R)i^p = 2.330, M^ = 3. 00; a = 0°. 



82 



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AM«, -0.1 



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2.30 



2.32 



2.3^ 



2.36 



2.38 



2.i^-0 



VR/iip 



Figure 15.- Sensitivity to Mach number decrement, I.50 D inlet with vor- 
tex generators; bleed exit setting B, 1^ = 3. 00, a = 0'. 



83 



































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1.00 
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.80 
.70 
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Apt 


















1.50 


D inlet with 




^:r— 


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bleed exit setting B 

D Modified I.75 D inlet, 
bleed exit setting A' 




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8 



10 



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a, deg 
Figure 1?.- Maximum performance at angle of attack, Mqo = 3.00 



12 



85 



1.0 






^Pt; 



• 5 

.8 















a 
O 





(x/R)iip 
2.330 










O-Q- 




A 5 2.ii30 
O 8 2.680 








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^ 




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^ 


4 







.80 



.84 



.88 



.92 



•96 



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in2 



Figure l8.- Supercritical performance at angle of attack, I.50 D inlet 
with vortex generators; exit setting B, Moo = 3-00. 



86 



1.1 



1.0 



\ ^oo/max. 



•9 



























































i 


JHoK 


>-<H 


UX, 


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9 


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^ 


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O 1.50 I* inlet with vortex generators^ 

bleed exit setting B 
D Modified 1-75 D inlet, bleed exit 

petti ncr A' 




\ 










h 








A 


Initial 1 


• 75 r 


) inlet 













m- 



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■ _LU 






























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-i 


^ 


•D — 

o— 


^ 


-s 


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\ 


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a 


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^ 












\ 
































.01; 























A 



Pt2 




,8 



1.2 



2.i^ 



1.6 2.0 

Moo 

Figure I9.- Off -design maximum performance, a = 



2.8 



3.2 



87 



Pt2 



1.00 



• 90 



C3 C] [ 


>-f 


'--t 


)-^ 


N 


1 




O MinimiJin Cj) 

D C-n for maximuir} 


N 


\ 


N 






L 


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FN " ^Da^ 




^ 


\ 


^ 


N 


/ 







































m2 
"mZ" 



.48 



AU 



.40 



• 36 





\ 


/ 


y 


Inlet maximuin theoretical capability 




\ 


/ 












/ 










c 


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c 


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] 














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N 




J* 


V 














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L 


J 























% .1 













/ 


^ 




















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M 


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c 




\ ( 


r 


X 


X 










^~ 


— — 


— - 



























1.0 



1.2 



1.4 1.6 



Figure 20.- Transonic performance; bleed exit setting B; a = 0' 



88 



3.60 



3.40 



3-20 



3.00 



(ti. 



lip 



2.80 



2.60 



2.U0 



2.20 





1.55 






















\ 


1.75 
























\ \ 


\^- 


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\ 


\ 






















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M 


k'- 


25 




















\ 


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V 


\\ 


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\ 


\\ 


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2.75 




















\ 


\ \ 


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\\ 


\ \ 


\^ 


20 




















\' 


\\ 


\ 






















\ 


\\ 
























\ 



























.7 



• 9 1.0 



Figure 21,- Inlet theoretical mass-flow ratio^ a = 0*. 



89 



^ta 



Pt. 



,80 



.76 



.72 



.68 



.61+ 



.60 











-n ^ 



D 
A 
3 


Blee 


d exi 


.t setting A 




i 




7 






Bleed exit setting a 
Bleed exit setting C 
n A See Table II 




* 




F 








X r 


s 


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T 






















i 


5i 

c 


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C 


-) 






















i- 


^ 


( 


► 






















c 




























^ 


)— 





















^Pt. 



.1+0 



.30 



.20 



.10 





1 


p 














































_A J- 


] Q 






















— n^ 


3— c 
























/! 


>^ 


y. 






















^ 


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-stli- 


A 
























IN 







































.Ok .06 .08 .10 .12 .Ih .16 

moo 

(a) (x/R)iip = 2. 330; Moo = 3.20. 

Figure 22.- Supercritical performance, I.50 D inlet with vortex gen- 
erators; a = 0°. 



90 






.92 



.88 



.81+ 



.80 



.76 



■72 



AO 



.30 




^Pt 



'2 .20 



,10 



.0^ 



12 



.06 



.08 



O Bleed exit setting A 

n Bleed exit setting B 

A Bleed exit setting C 

3 11 A See Table H 



























-1 


















^ 


r V 


























































A-^ 


JtA 1 




















"^ 


^ 


QXI 


^n 


-<:k: 





























.10 
"^1 

nioo 



,12 



.11+ 



.16 



(b) (x/R)-Lip = 2.330, M<„ = 3.00. 
Figure 22.- Continued. 



91 






.96 



.92 



.88 



.Qk 



.80 



•76 



,1+0 



.30 











































1 


















A' 


/^ 


o°i 


loC 


r3 






XM 


X 1 










y 


^ 




^ 


















f' 


/ 


f 






















' 






















z^ 


r" 






















^c 





Bleed exit setting A 
D Bleed exit setting B 
A Bleed exit setting C 












6 














o 


a 


A 


3ee Table 


II 



Apt 



2 .20 



,10 



.04 




































































































































% 


U- 


L= 


^. 


R^ 


V 


<D 
















Dt;- 


-!<5i: 




^ 

































.06 



.08 



.10 

"bl 

moo 



,12 



.14 



,16 



(c) (x/R)iip = 2.420, M^ = 2.75. 
Figure 22.- Continued. 



92 



"too 



^Pt. 



•96 



.92 



.88 



.dk 



.80 



.76 



.ko 



.30 



.20 



,10 



































^^0^^ 














/ 


/ 


/ 


^ 
















/ 




i 


r 


















f 




/ 




















ii 






</ 






















a 




























Bleed exit setting A 
D Bleed exit setting B 
A Bleed exit setting C 


























3 


n 


A See Table H 









































































































A 
























1a 


%. 




V 




















"5^ 


^ 


-ob 


l?v- 


^^ 


D 































.Qh 



.06 



.08 



.10 
moo 



.12 



.111 



.16 



(d) (x/R)-L-i^p = 2.600, M„ = 2.50. 
Figure 22.- Continued. 



93 



1.00 



.96 



.92 






.88 



.8li 



.80 



.ko 



•30 





























































./^, 


.^ 


/-^ 


^ 


P 












K 


^ 


[r-^ 

^ 




^ 














n 


/ 


;^ 


sy 
















I 


/ ' 


d 


/ 




















































O Bleed exit setting A 
D Bleed exit setting B 
A Bleed exit setting C 


























3 


n 


^ 


See Table 


11 



^Pt2 .20 



.10 







































































































c 
























.^ 


-^ — L 


y'^:::!^ 


ro 
















I 


^ ' 




^ 


^ 
^ 


^ 


^D 


^, 


. ^Ti 






















C 


y^ 







.04 



.06 



.08 



.10 

I"t)l 

IDoo 



,12 



.11^ 



,16 



(e) (x/R)iip = 2.860, Moo = 2.25. 
Figure 22.- Continued. 



3h 



1.00 



.96 



.92 



Pt. 



.88 



.8li 



.80 



























































M 






^ 


x> 














/ 


/ 


/ 


/^ 
















/i 


vi 


/ 


J 






















J 


yJ 


















































Bleed exit setting A 
D Bleed exit setting B 


























A 




/I See Table H 



.i^O 



.30 



^Pt2 .20 



,10 



.°0* 































































































































A 


ft E 


ND- 


O-^ 


^ 


















\ 




^T^ 


^ 


^»^ 
























XiP 


■o 









.06 .08 .10 .12 

'"bl 
moo 

(f) (x/R)iip = 3.100, Moo = 2.00. 

Figure 22.- Continued. 



,11+ 



,16 



95 



1.00 




^Pt2 .20 




moo 



(g) (x/R)iip = 3.320, M^= 1.75. 
Figure 22.- Continued. 



9e 



1.00 



Pt. 



• 96 



.92 



.88 



.81+ 
















































































^-^ 


w'^ 




< 


r^ 














1 


1^ 

/ 


w^ 


f 


i: 


jj 














f 


/ 


y 


















I 


J 


K 


/ 




















V 


/ 








: Bleed exit setting A 
D Bleed exit setting B 
A Bleed exit settins C 




3 


/ 




















9 


a . 


4 £ 


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II 



^Pt 



.ifU 


























.30 


















































2 .20 


















































.10 


























z: 


^■dsQ 


^ 


3-Q^ 


C^ r 




jO 


















V, 


■^ 


Ki-rJ tijuj 


^ 












n 


oCff 


> 



.01+ 



.06 



.08 



.10 

%)1 

moo 



,12 



.lU 



.16 



(h) (x/R)iip = 3.^20, M„= 1.55. 
Figure 22.- Concluded. 



97 



Pt. 



Pt 



A 



.96 
.92 
.88 
.8^ 
.80 
•76 

.ko 

.30 

Pt2 .20 

.10 

















A 


Bleed exi 


t setting 


A 














A isieed. exit setting U 
<• A See Table II 


















,^r^ 


1 












A . 


W^ 


L 


^ 


^ 














i 


^ 




/ 


















J 




/ 


(T 


















f 


( 


/ 


















J 


1 






















A 




























(1 













































^ 


V 


\ 






















\ 


\ 






















\ 
























Z 


^ 


-2S~^ 


^^^ 


^, 


























^^ 


D-GG 


) 





















































.01+ 



.06 



.08 



.10 



,12 



.11^ 



.16 



(a) (x/R)-Lip = 2.330, M^ = 3-00. 



Figure 23.- Supercritical performance, I.50 D inlet without vortex gen- 
erators ; a = " . 



98 






.96 



.92 



.88 



.8^ 



.80 



.76 



Ao 



.30 



^Ptp .20 



.10 

















A 


Bleed exit setting 


A 














3 A See Table II 














4 


^ 


^<^ 














A 


f 




















/ 


/ 






















"/ 


i 






















/ 
























(1 
























A 


















































\ 
























I 
























N 


















\ 


\ 


G. 






















^ 


A 




N, 
























\ 


^ 


1 





















































.01+ 



.06 



.08 



.10 

°'1)1 



.12 .114- 



(b) (x/R)iip = 2.1+20, Moo = 2.75- 
Figure 23-- Continued. 



,16 



99 



.96 



.92 



Ptc 






.8^ 



.80 



■76 





































aA-^ 


r 


r^ 


a:y^ 


)3 












/ 


^^ 





^ 


















/ 




/ 


















y 


( 


/ 


/ 


















A 




/ 
























i 


















































O Bleed exit setting A 














A — — 
9 


cxeea exii: seT:T:xng u 
A See Table II 



.1^0 



,30 



^Ptp .20 



.10 





































Q 




















A 




\ 




















^ 


V 




\ 




















\ 




\ 






















\. 


-A 


Q-C 


^o. 


Y^-^ . 


o 






















MZ>< 


r 





























.OU 



.06 



.08 



.10 



.12 



m- 



bl 



ffloo 



(c) (x/R)iip = 2.600, Moo = 2.50. 
Figure 23.- Continued. 



.W 



,16 



100 



1.00 



.96 



.92 



Pt, 



^Pt 



.88 
.81+ 

.80 
.^0 

• 30 

2 .20 

.10 















O 


Bleed exl 


t setting 


A 














A ±5_Leea exit setting U 
(J A See Table H 












A 






r^- 












^ 


'^ 






^ 














/ 


r 


/ 


^ 
















i 


f 


( 


/ 







































































































































































































































i 


V 




2t6. 


_ y% 






















:>-^^ 


2^D- 






■%G 


b 































.ol^ 



.06 



.08 



.10 

IDoo 



.12 



(d) (x/R)iip = 2.860, Moo = 2.25. 
Figure 23-- Continued. 



.\h 



,16 



101 



1.00 



• 96 






■92 



.88 



.81+ 



.80 



.1+0 



• 30 



























































l^ 


k 


,^" 














/ 


/ 




/ 
















^ 


/ 




(/ 


















£k 




</ 








































































O Bleed exit setting A 














3 


^ 


See 1 


feble 


II 



^Ptp .20 



.10 





























































































































A 


A, 


CD- 


Ox- 


^ 


















^^ 


^V^ 


li 


^ 


^<^ 


-o 

































.oil 



.06 



.08 



.10 

IHoo 



,12 



.11+ 



,16 



(e) (x/R)iip = 3.100, Moo = 2.00. 
Figure 23 •- Continued. 



102 



1.00 



.96 



.92 



Pts 



Pt„ 



,88 



.dk 



.80 















o 

A 


Bleed exit setting 


A 














A i3±eea exi"G seating u 
<• A See Table TL 






/ 


f 




/ 


» 
















/ 




^ 


i» 


















f 




i 




















i 


<d 


f 








































































































h ■■■ 









.^u 


























• 30 


















































■^Ptp .20 




















































10 






^ 


r\ 






















i 


\ 




oxx 


Q^ 


) 












n 



























.Oi+ 



.06 



.08 



.10 

"'bl 

IHoo 



.12 



(f) (x/R)iip = 3-320, M^= 1.75. 
FigTire 23-- Continued. 



,11^ 



,16 



103 



1.00 



Pta 



^Pt, 



.96 



.92 



.88 



.81+ 



.80 



.ko 



.30 



.20 



,10 
































A ^ tl^ -/ 


'^. 


C^ 












1 


f-^ 


■^ 


/ 


(. 


) 














I 




/ 




















1 


H 


/ 


















— ^ 




/ 






















G 


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-:d- 


^ 


1 




a\ 






• 


\s\ 




o 


CO 


MD 


tl 


Q) 


• 




^ 


CO 


8 


^ 




-p 


bO 




ft 


e: 




CM 




A < 


-iJ 






Ift 





CO 
OJ 



OJ 



CVJ 



VD 



VO 


OJ 


00 


-:t 


o 


oo 


oo 


OJ 


OJ 


OJ 



M3 



OJ 



CO 



, 8 

ft ft 



1^7 

















o 
cd 


















"i 






















— 












] 




/ ' 


































I 


































[] 




































9 




































q 






















1 








t 


M 












































c 


























/ 












? 




O Centerbody 
□ Cowl 


















/ 












? 




















/ 












1 


















i 


( 












1 


















/ 














1 
















-p 

O 

1 






7 














1 




1 














\ 




/ 














1 


















._. ^ 




1 
















K 
















ft 




\ 














d 


Q 




















\ 
















1 




















\ 
















9 




















\ 
















T 






















\ 














S 






















\ 














A 






















\ 














Y 






















\ 














6 






















\ 







































\ 












o 



CO 






M3> 






^ 






VD 






O 






vo 






MD 






• 






IXN 






OJ 






• 






LTN 






CX> 


LTn 






\s\ 




-^ 


O 

6 
II 




-^ 


8 




-=J- 


^ 


1 




H 


H 


X 


fi:; rQ 


O 




s 


S=! 


o 


•N 


o 


^ 


S" 






CO 


• 




• 


LTN 




o 


OO 


MD 


II 




on 


8 







-p 


w 




ft 


e: 




w 




OJ 


-p 
Ift 





CO 

CM 



OJ 



o 

CM 



vo 



VO 


cvj 


CO 


-^ 


o 


on 


OO 


CVJ 


cu 


CVJ 



VD 



CVJ 



CO 



ft ft 



Ikd 



1.00 






,80 

,70 

,60 
.50 


















Bleed exit setting A 




==^"^/ 










D Bleed exit setting B 
A Bleed exit setting C 
3 a A See Table U 




^^ 


K 


V 












^ 


\ 


1 






















> 


\ 
























^ 


\ 
























> 


V 
























\ 


I 









^Pt. 




a, deg 
(a) M^ = 3.00. 

Flgiire 36-- Maximum performance at angle of attack, I.50 D inlet with 

vortex generators . 



Ih9 



1.00 



.9C 






.80 



'00 /max. 

.70 

.60 
.50 

M 
.30 

^Pt2 .20 
.10' 


















Bleed exit setting A 


3 




■ 








D Bleed exit setting B 
A Bleed exit setting C 
3 n A See Table 11 


i 


~— ^ 


b^- 






^ 


s 












X 


\ 


k 
























\ 




























V 
























N 


i 


















































































Figure 36.- Continued. 



150 



(■s4 



• KJ\J 
















n 

A 
3 


Bleed exit setting A 


c 


Y 


=_ -^ 


k 


^ 






Bleed exit setting B 
Bleed exit setting C 
a A See Table H 


t 

• 90 




■^ 


N 








N 


\ 


V 


.80 










> 


























A 


k 












.70 
















^ 


3 
































.60 



























Ap^ 





.30 
.20 
.10 

i 






































































^ 


5 








2 










J 


^ 


^ 
























KX 

; 
















i^ 


^ 


^ 


^ 


y 


















^ ^ 


y^ 















































5 4 6 

a, deg 
(c) r4<„ = 2.50. 

Figure 36.- Continued. 



10 



12 



151 



\ ^00 /max. 



1.00 



.90 



.80 



.70 
.60 

.30 

^Pt2 .20 



.10 


















Bleed exi 


.t se 


tting A 

j_ j_ • . -n 


^^ 


^ 


^ 


:^. 






A Bleed exit setting C 
d n A See Table H 










^ 


L 












^ 


v^ 


^^^y 


\ 






















^Sl 

































































































































































/ 




^^ 


^ 


\ 



















pS 


^^ 














/f 


^ 


^ 


y^ 


















^ 


r^ 













































> h 6 

a, deg 
(d) M^ = 2.25. 

Figure 36 •- Continued. 



10 



12 



152 



tei.. 



1.00 



.90 



.80 



.70 



,60 



^i*-^ 
























t«-^«5^ 


^ 


^ 


^. 
























^^ 


^ 


fc^ 
























^^5 












































Bleed exit setting A 














A Bleed exit setting B 














3 


a 


A . 


Dee Table 


3 ^ 

II 



,M-U 


























.30 








































r 


1 








Ap+. 20 














^ 


^ 


J ■ ■ 
















^ 




p 


^^^^ 












10 




J 


A 




^ 
















i 


^ 


^ 


r 




















\ 

n 



























? 4 6 

a, deg 
(e) M^ = 2.00. 

Figure 36.- Continued. 



10 



12 



153 



1.00 



.90 






00 /max. 



.80 



.70 



,60 



^ 
























"^ ^ 


\— 


— _ 


^=^ 


1=^ 




























r ■ 








































































O Bleed exit setting A 
D Bleed exit setting B 
A Bleed exit setting C 


























3 


CI 


A ! 


3ee Table 


11 



,U0 



.30 



^Ptp .20 



,10 

























































































/ 


i 


















^^ 


^ 


] 
) 










^ 




. 


-^ 


^ 




/ 










.^ 


=— ^ 


1==^ 


^ 


jp,^— '.. 


^^ 














IF' 

























4 6 

a, deg 

(f) M,, = 1.75. 



10 



12 



Figure 36'- Continued. 



15^ 



\ ''oo /max . 



1.00 



.90 



.80 



.70 



.60 



^ 




.^ 






■ 






















i^ 


^*^ 


^ 


} 




























































































Bleed exit setting A 
D Bleed exit setting B 
A Bleed exit setting C 





























a 


A See Table 


H 



• '-l-W 


























.30 


















































^Pta .20 








































r 


1 








10 
















^ 


) 








^ 


fc== 


=H 


^ 


^ 


^ 


K 

















} 

























2 k 6 

a, deg 
(g) Moo = 1.55- 
Figure 36.- Concluded. 



10 



12 



155 



Pt, 



Pt, 



00 /max . 

















o 

A 


Bleed exit se 


tting A 


• 90^ 




^ 


K 


^^ 






C» A See Table H 


.80 








N 


X 
























^ 


s, 


























\ 














•7u 
















\ 










.60 
















^ 


\ 






















(^ 


) 








r-r\ 



























^Pt. 




Figure 37,- Maxuitium performance at angle of attack^ I.50 D inlet with- 
out vortex a-enerators. 



156 



1.00 



,90. 



\ ^00 /max. 



,80 



•70 



.60 















o 


Bleed exit setting A 


iz= 




^ 






A iileed. exit setting C 
3 A See Table H 






M 
























N. 
























\ 


s. 
























\ 


V 
























\ 


:> 

































^T>+„ 




2 k 6 

a, deg 
(b) M„ = 2.75. 

(b) Figure 37.- Continued. 



10 



12 



157 



1.00 



.90 






oo/max. 



,80 



• 70 



,6o 















O 

A 


Bleed exi 


t setting 




0) 


( 


^. 








3 A See Table 11 


is 


i 








X 


s 
























\ 


k=s 
























^ 


^ 
























^N. 

























































Ao 



.30 



^Ptp .20 



.10 

















,^ 


:^ 






















;^ 


) 
















/ 


K^ 






















/:; 


/I 


















^ 


^ 


/ 
















y^-^ 


^ 


^;^ 


/ 


















^\ 


^^ 


/ 











































: k 6 

a, deg 
(c) M^ = 2.50. 

Figure 37-- Continued. 



8 



10 



12 



158 



\ ^00 y max. 



1.00 



.90 



.80 



Ap^ 



.70 
.60 

.ko 

.30 

2 .20 

.10 

















A 


Bleed exit setting A 


^~~" 


"^ 


^ 


-^ 






A Jiieea exit setting U 
(• A See Table U 








~~" 


==^ 


•^ 
























V 




"N 


> 






















^ 


i 

































































































































































,/ 






, ^ 


) 












^ 


^^ 


i 


r 


-^ 












,..,,^^ 




^ 


,^ 


y 
















— 

















































; h 6 

a, deg 
(d) M^« 2.25. 

Figure 37.- Continued. 



10 



12 



159 



( 



hi 



'00 / max , 



.uu 


^ ^ . 














A 


Bleed exi 


.t setting A 


.90 


■^ 


N 


fc^^ 


^ 






3 A See Table H 








"^ 


^ 


























z 






t-^ V 


) 








.80 




^^ 


























.70 


















































Cr\ 



























Ap^ 





.30 

.20 

.10 

C 
























































































/ 








;i 








cd 










^ 


^' 




















.^ 


^ 




















v-^ 


^ 


r 















































(e) M„ 



a^ de^ 



2.00. 



8 



10 



12 



Figure 3?.- Continued. 



160 



1.00 



.90 






,80 



.70 



.60 



<^___ 


























""" 


k 




"-==< 


^ 


^^^ 


























^ 


i 




























































































O Bleed exit setting A 














9 


A See Table II 



Ap+_ 



.ho 



.30 



.10 

























































































1 


\ 






















A 


) 
















^ 


cr:^ 




y 












===^ 


)F= 


===== 


==^ 


r 














C)"^ 

























4 6 

a, deg 
(f) M^= 1.75- 

Fig\ire 37.- Continued. 



8 



10 



12 



161 



1.00 



.90 



l^t^i 



'00 /max. 



.80 



.70 



.60 



H- 
































^=r-a^ 




^^ 


^^ 


i 




















































































































Bleed exit setting A 














3 


^ 




See ' 


rable 


II 



.1^0 



.30 



^Pt2 .20 



.10 

















































































































K^ 


















J 




^ 


y 










^> — 


^ 






^ 


^ 





































5 U 6 

a, deg 
(g) M„ = 1.55. 

Figure 37 . - Cone luded . 



8 



10 



12 



162 



1.0 




















1 














C 


^HDC) 


S2Es£t 




















^^^^©c 


"1 


\ 










^A 








!; 


i 










'i 


^^^"^ 


—A 
4 






% 














\ 


>^ 










«5v> 


fta /\ 








a, deg (x/R)iip 
O 2 . 420 






i 








D 

A 

o 


2 

k 

6 


2.4i+0 
2.620 
2.800 



^Pt. 























.<9^ 


-^ 








\ 








■y 




/vA^ 


^ 

C 


^ 




□ 










^J-u 




I3^><5E 


K3-G@ 


i 





• 72 



76 



,80 



,84 



,88 



•92 



in2 



(a) M^ = 2.75 

Figure 38.- Supercritical performance at angle of attack^ I.50 D inlet 
with vortex generators; exit setting B. 



163 



1.0 



• 9 




































Eb- 


eWS 


^ 




















^ 


^ 






i 


^^ 












i 














> 










< 


% 


^>- 


/X/v 




















v.*0 






a, deg (x/r)ij_p 
O 2.600 














1 1 

A 

o 


5 
8 


2.810 
2i920 



^Pts A 





























^ 














< 


>^ 


A ^ 


St*- 


— A- 


J^ 




g:©^ 


JP-^ 






I 


£Sr^— ^ 






□D^ 


^ 


^ 





,6)+ 



.68 



•72 -76 



(b) M„ = 2.50 
Figure 38.- Continued. 



,80 



.Qh 



l6h 



1.0 






.8 































C 






^ 












^ 






fc^ 


^^ 










^ 


^ 


— A 












i 




2^.— 


'X 


















"'K^h-^ 


s/ 
























a, deg (x/R)iip 
O 3 . 360 














D 
A 

O 


2 

5 
8 


3-380 
3-^90 
3-560 



.8 



^Ptp .h 



L 

• 52 













































^ 


:/^ 


.. A 




















20r^-*^ 




^;S^ 


5S^ 


=C5lJ:S 


-□ 





■ 56 



,60 



.6ii 



m2 



(c) Moo= 2.25 
Figure 38-- Continued. 



,68 



•72 



165 




^Ptp A 



^A 



.1+0 



.hk .k8 .52 

(d) M^ = 2.00 
Figure 38.- Continued. 



56 



,60 



166 



1.0 



-t2 



Pto 



.8 















a, deg 


(x/R)iip 








%rL. 






O 
D 2 


3-820 
3-820 








1% 










4 


\ 


K 




A 5 
O 8 


3-820 
3-250 






%. 


\ 


















^\ 




d 
















<■ 


K 































































































.8 



^Pt2 .k 





















■ ■ 


























,r,c/^ 


^ 



































• 36 



Ao 



.i^U 



A8 



m2 



(e) M«,= 1-75 
Figure 38.- Concluded. 



■ 52 



• 56 



16? 



Pt, 



Pt 



1.00 



• 96 



.92 









1 — °p — 1 


=^ 


J 


^ 






















n\ 














































CD, 









^ 










d 


/lip 








4 


\ 








3-65 
D 3.50 
A 3-35 










^. 


\, 














\ 


^^ 




















^ 


V \ 


















~* 


^ 


^ 


















\ 


^ 


^ 





























.3 



mi 



m^ 



(a) M^ = 0.60. 
Figure 39«- Transonic total-pressure recovery and additive drag, a 



168 



Pt. 



1.00 








1 do — 


^■^t] 




^ 






. .96 
















^ 


























.92 


















A 





^n 



'a 




m. 



(b) Meo = 0.70. 
Figure 39.- Continued. 



169 






1.00 



.96 



•92 



.88 









' 1 


*t>-= 


" L 


r-y 


n^ 




















1 


1^ 




















\ 




















^ 




















\ 




















h> 





-D„ 









i 

r 


\ 








(-1 


/lip 










\\ 


V 






O 3.65 
n 3-50 
A 3.35 










^\ 


\ 














\ 


\>^ 


k 


















\t 


^N 


\ 




















^> 


^ 


















^ 


f 





























mi 



(c) M„ = 0.80. 
Figure 39.- Continued. 



170 






1.00 



• 96 



• 92 



.88 



.81+ 






r-r. 




mi 
moo 
(d) M^ = 0.90. 

Figiore 39.- Continued. 



171 



1.00 



.96 



Ptp -92 



Pt. 



.88 



.8k 



— 1 



CD. 




(e) M„ = 1.00. 
FigTore 39.- Continued. 



172 



1^ 



1.00 



.96 



.92 



.88 



,8U 



,80 















^r^> 






- 












\ 




















\ 








































% 




































n 










































I 


















t 


1 





Cd„ 



















a 
















\ 




o 3.65 
□ 3.50 

A 3.35 














\ 


\ 














\ 

( 


kN 


y^L 


















\\ 


2? 


















^ 


J" 













































.2 



.5 



(f) Hx,= 1-05. 
Figure 39'- Continued. 



173 



1.00 



• 96 



Pt, 



■ 92 



.88 



.8k 



.80 



() 

1 1 \ \ 1 ^ — I 1 



Cd. 




mn 



nin 



(g) M = 1.10. 
Figure 39* - Continued. 



17^ 






1.00 



■ 96 



■ 92 



.88 



.8ii 



,80 















— t 


n 


















\ 
















\ 














' 


















Y 


















A 

9 




















































T 

n 


















i 
















C) 





'D« .2 



















(i 


r) 














^ 


s 


O 3.65 
□ 3-50 
A 3.35 
















1 \ 














[ 


V 


V\ 


















-> 




















^ 


P 













































• 1 



.3 .^ 



mi 



Mn 



(h) M^ = 1.15. 
Figure 39*- Continued. 



175 






1.00 



.96 



.92 



.88 



.8ii 



.80 



.76 









\R 


'l±v 




^ 


\ ^ 


A 










3-65 
D 3.50 
A 3.35 






\ 


1 














\ 




















\ 





































































































c, 




















\^ 


% 














































^Da 



.1 















^ 




















\ 


\ 
















^ 


\\ 




















\. 


h 















































mi 



m^ 



(i) M^ = 1.20. 
Figiire 39-- Concluded, 



.5 



176 



3.0 



CO 
Q 
O 






4^ 



CO 

I 

o 

H 
X 
CD 

-p 

•H 

+^ 

H 
< 



2.9 



2.8 



2.7 



.2i^ 









J^ 


^ 


' 


-^ — 


?^ 










^ 


^ 


^ 






X 


\ 








^ 












\^ 






1 














\ 


y 














(r/iip 




^ 














n 3 

A 3 


•50 
• 35 




\> 



.28 



■ 32 



.36 



Ao 



.\h 






;a) Net propulsive thrust, ¥^ = 0.60. 




(b) Flight profile. 
Figure ^4-0.- Transonic optimization. 



A-2658 



NASA-Langley, 1967 



177